Nose Landing Gear Oh

T.O. 4S2-23-3 TECHNICAL MANUAL

OVERHAUL INSTRUCTIONS STRUT ASSEMBLY NOSE LANDING GEAR

AND BUILDUP INSTRUCTIONS NOSE LANDING GEAR ASSEMBLY

(ATOS)

LOCKHEED AERONAUTICAL SYSTEMS (98897) F33657-744-0226 F33657-86-G2000

DISCLOSURE NOTICE: This information is furnished upon the condition that it will not be released to another nation without the speclfic authority of the Department of the Air Force of the United States, that it will be used for military purposes only, that individual or corporate rights originating in the information, whether patented or not, will be respected, that the recipient will report promptly to the United States, any known or suspected compromise, and that the information will be provided substantially the same degree of security afforded it by the Department of Defense of the United States. Also, regardless of any other markings on the document, it will not be downgraded or declassified without written approval of the originating United States agency. DISTRIBUTION STATEMENT C: Distribution authorlzed to U.S. Government agencies and their contractors, administrative or operational use, 1 0 July 1987. Other requests for this document shall be referred to OOALC/ 510 CBSS/GBHC, Hill AFB, Utah 84056-5820. WARNING: This document contains technical data whose export is restricted by the Arms Export Control Act (Title 22, U.S.C., Sec 2751 et seq) or the Export Administration Act of 1979, as amended (Tltle 50, U.S.C., App 2401et seq). Violations of these export laws are subject t o severe criminal penalties. Disseminatein accordance with provisions of DoD Directive 5230.25. HANDLING AND DESTRUCTION NOTICE: Comply with distribution statement and destroy by any method that will prevent disclosure of contents or reconstruction of the document.

Published under authority of the Secretary of the Air Force

22 MAY 1998 CHANGE 7

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9 MARCH 2007

T.O. 4S2-23-3

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INSERT LATEST CHANGED PAGES DESTROY SUPERSEDED PAGES

LIST OF EFFECTIVE PAGES NOTE: The portion of the text affected by the changes is Indicated by a vertical llne in the outer margins at the page Changesto illustratlonsare Indicated by minlature pointing hands Changes to wlrlng dlagrams are indicated by shaded areas

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Dates of issue for original and changed pages are: Original ........................... 0 ................ 22 May 1998 Change ............................. 1...............8 March 2000 Change ............................. 2 ....... 13 November 2000 Change ............................. 3 .......... 10 January 2002

Change ............................. 4 ........... 16 October 2003 Change ............................. 5............ 18 August 2004 Change ............................. 6 ...... 27 September 2005 Change ............................. 7............... 9 March 2007

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'Zero in thls column lndlcates an orlglnal Pago

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USAF

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TABLE OF CONTENTS

SectionPara

Page

I INTRODUCTION............................................................................................................................ 1-1 1-1 Identification ............................................................................................................... 1-1 1-2 Purpose ......................................................................................................................... 1-1 1-3 General Description................................................................................................. 1-1 Additional Models........................................................................................................ 1-2 1-4 Leading Particulars ............................................................................................... 1-2 1-5 I1 OVERHAUL INSTRUCTIONS ......................................................................................................2-1 Special Tools .............................................................................................................. 2-1 2-1 2-2 Disassembly .................................................................................................................2-1 2-3 Cleaning .......................................................................................................................2-1 2-4 Inspection, Repair, and Replacement ........................................................................2-2 2-5 Lubrication ................................................................................................................. 2-19 2-6 Reassembly ................................................................................................................ 2-20 2-7 Installation of Bushings in Torque Arms ................................................................2-20 III TEST PROCEDURE .......................................................................................................................3-1 Leakage Test ................................................................................................................ 3-1 3-1 Procedure .....................................................................................................................3-1 3-2 IV NONDESTRUCTIVE INSPECTION INSTRUCTIONS .............................................................. 4-1 4-1 General .........................................................................................................................4-1 Equipment and Materials ......................................................................................4-1 4-2 Inspection Procedures ................................................................................................ 4-1 4-3 4-4 Rejection Criteria ........................................................................................................ 4-1 V NOSE LANDING GEAR BUILDUP INSTRUCTIONS .............................................................. 5-1 5-1 General ....................................................................................................................5-1 5-2 Buildup Instructions ................................................................................................... 5-1 5-3 Subassembly Buildup ................................................................................................ 5-13 VI DIFFERENCE DATA SHEETS ..................................................................................................... 6-1

T.O. 4S2-23-3

LIST OF ILLUSTRATIONS Figure

Title

Page

Nose Landing Gear Strut Assembly .................................................................................... 1-2 Nose Landing Gear Strut Assembly ....................................................................................... 2-3 Plating of Nose Landing Gear Outer Cylinder ..................................................................... 2-9 Plating of Nose Landing Gear Piston ................................................................................. 2-10 Plating of Nose Landing Gear Fulcrum Assembly ............................................................. 2-11 Pulley Mounting Lugs Repair ............................................................................................... 2-16 Location of Seals ................................................................................................................ 2-21 Keyways ........................................................................................................................... 2-22 Installation of Bushings in Torque Arms ........................................................................... 2-24 Fulcrum and Cylinder Assemblies Magnetic Inspection Coil Locations and Conductor Positions .................................................................................................................... 4-2 Piston Assembly Magnetic Inspection Coil Locations and Conductor Positions................. 4-3 Nose Landing Gear Assembly ................................................................................................. 5-3 Manifold Assemblies .............................................................................................................. 5-14 Cylinder and Tubing Assembly........................................................................................ 5-19 Nose Landing Gear Strut Assembly. Part No . 7926487.10. Exploded View ....................... 6-9 Cylinder Assembly Inspection Coil Location and Conductor Position. Part No. 3303589-1...................................................................................................................... 6-12 Nose Landing Gear Strut Assembly. Part No . 7926829-10............................................. 6-16 Nose Landing Gear Strut Assembly. Part No . 371671.1. Exploded View .........................6-20 Replacement and Reconditioning Dimensions..................................................................... 6-25 Outer Cylinder Corrosion Removal ................................................................................. 6-28 Nose Landing Gear Strut Assembly. Part No . 3303591.1. Exploded View ....................... 6-40 Nose Landing Gear Strut Assembly. Part Nos. 3303591.3.3314203.3. and 3316500.13. Exploded View ............................................................................................... 6-44 Replacement and Reconditioning Dimensions..................................................................... 6-49 Cylinder Assembly Inspection Coil Location and Conductor Position. Part Nos. 3303589-3and 3303589-5.................................................................................................. 6-57 Nose Landing Gear Assembly. Part No . 396175-17.......................................................... 6-67 Manifold Assemblies for Part No. 396175-17...................................................................... 6-69 Nose Landing Gear Assembly. Part No . 3001011-3............................................................ 6-75 Manifold Assemblies for Part No. 3001011-3...................................................................... 6-80 Nose Landing Gear Assembly. Part Nos. 388067-7and 388067-9.................................... 6-86 Manifold Assemblies for Part Nos. 388067-7and 388067-9............................................... 6-90 Nose Landing Gear Assembly. Part Nos. 3303595-1and 3303595-5................................ 6-96 Manifold Assemblies for Part Nos. 3303595-1and 3303595-5......................................... 6-103 Nose Landing Gear Assembly. Part No . 3314205-3......................................................... 6-110 Manifold Assemblies for Part No. 3314205-3.............................................................6-119

T.O. 4S2-233

LIST OF TABLES

Number

Title

Page

Leading Particulars ................................................................................................................. 1-2 2-1 Special Tools.......................................................................................................................... Replacement and Reconditioning Dimensions.......................................................................2-4 Repair and Rework ................................................................................................................. 2-7 Vacuum Cadmium Plate Areas ..........................................................................................2-8 Rework Criteria .....................................................................................................................2-13 Circular Magnetization ......................................................................................................4-4 Longitudinal Magnetization.................................................................................................... 4-4 Circular Magnetization .........................................................................................................6-12 Longitudinal Magnetization............................................................................................ 6-12 Replacement and Reconditioning Dimensions................................................................. 6-18 Vacuum Cadmium Plate Areas ............................................................................................ 6-21 Allowable Service Dimensions .............................................................................................. 6-23 Allowable Service Dimensions .............................................................................................. 6-46 Circular Magnetization ......................................................................................................... 6-56 Longitudinal Magnetization.................................................................................................. 6-56

iii/(iv blank)

T.O. 4S2-23-3

SECTION I INTRODUCTION This overhaul and buildup instructions technical manual is issued to instruct U.S. Air Force maintenance personnel in the disassembly, repair, reassembly, and testing of the nose landing gear strut assembly, part No. 363590-1A. (See figure 1-1.) Other nose landing gear strut assemblies are covered by difference data sheets in section VI of this manual. Information for identifying and ordering procurable spare parts for the strut assembly is given in T.O. 482-23-4, Illustrated Parts Breakdown for Nose Landing Gear Strut Assembly. The operation of the strut assembly as a functional part of the landing gear system is described in the applicable airplane maintenance manual. Buildup instructions for nose landing gear assembly, part No. 396175-13, are provided in section V. Additional nose landing gear assemblies are covered by difference data sheets in section VI. 1 PURPOSE. The nose landing gear strut covered in this technical manual is the oleo-pneumatic type using both hydraulic fluid and compressed air to produce a controlled resistance to aircraft takeoff and landing shocks. The strut is composed essentially of a telescoping piston and cylinder, the relative movement of which forces the hydraulic fluid through an orifice contained within the upper chamber. When the aircraft is being taxied, the loads developed are carried to the structure through the medium of the compressed air contained in the upper chamber of the strut. The air under pressure also serves to extend the strut to its normal static position in readiness to receive the next compression load. The impact energy of aircraft landing is mostly absorbed by both the compressed air and the hydraulic fluid dissipated through the strut walls in the form of heat. 1-3. GENERAL DESCRIPTION. a. The fulcrum assembly is the main support and pivots the nose landing gear. b. The shock strut consists of an outer shell (the cylinder) and an inner telescoping member (the piston). The wheel axle is an integral part of the piston. 1-1. IDENTIFICATION.

c. The steering collar is attached to the cylinder and lugs are provided for the attachment of the steering torque arm. d. Fixed packing glands, with packings, are designed to seal the piston and cylinder.

e. An air valve assembly consisting of a filler plug, air valve, and valve cap is located at the top of the cylinder to provide a means of filling and inf lating the strut. f. The top piston bearing is phenolic or Tefloncovered aluminum. The lower bearing is aluminum bronze or Teflon-lined aluminum. g. A bulkhead is located in the piston to seal the lower end of the piston. h. A scraper ring is installed in the gland nut to provide a means of keeping foreign matter from the packing gland.

Use of incorrect fluid may result in swelling and deterioration of all packing~ in the strut. Exercise care at all times to guard against mixing two different types of fluid which may cause the formation of a gummy substance and may coat the inner wall of the strut resulting in the malfunctioning of the unit. In case of accidental substitution or mixing of two different hydraulic fluids, flush the strut and clean it thoroughly. i. The strut is provided with an instruction plate. The condensed instructions deal with filling, inflating, deflating, and the correct type of hydraulic fluid to be used. NOTE

When checking the fluid level, be certain that the strut is in the fully compressed position. Unless the strut is carefully positioned, incorrect indication of fluid level may result. j. For proper operation of the strut, hydraulic fluid must be maintained at the correct level. The level of the fluid should be such that with the shock strut fully compressed, the fluid is just level with the filler plug boss.

T.O. 4S2-23-3

NOTE

When a small amount of fluid is being added for partial refilling, it will not be necessary to move the strut through its stroke in order to remove trapped air. k. When initial filling is being carried out, move the strut through two or three complete strokes while the strut is in the vertical position in order to remove any air pockets that might be trapped in the cylinder assembly.

1-4.

ADDITIONAL MODELS.

Sections I, 11, III,and

IV of this manual contain overhaul, test, and inspection instructions for the nose landing gear strut assembly, part No. 363590-1A. Overhaul and test instructions for additional models are provided in section VI by use of difference data sheets. The additional models included in section VI are listed at the beginning of the section and have the same procedures given in sections I1 and 111, except for the specific differences noted by the applicable difference data sheets. 1-5.

LEADING PARTICULARS. Table 1-1. Leading Particulars

Extended Length (approximate)........................................... 49.83 Compressed Length (approximate)............................................ 39.33 Length of Stroke........................................ 10.50 Normal Errtended Pressure ........................................ 300 (*lo) psi Weight ............................................... 179 pounds Fluid Capacity (approximate).............................. 3.3 US quarts

Figure 1-1. Nose Landing Gear Strut Assembly

T.O. 4S2-233

SECTION II OVERHAUL INSTRUCTIONS 2-1.

SPECIAL TOOLS. Table 2-1. Special Tools

PART NO. 755116-1 404226-1 404225-1 404224-1

NOMENCLATURE Screwdriver Guide Holding Rod Wrench Assembly

At no time is heat to be applied to any major landing gear component to facilitate removal of a frozen bolt or pin. Ensure temperature of landing gear component during drilling operations is maintained at or below 250°F.

FSCM 98897 98897 98897 98897

2-2. DISASSEMBLY. (See figure 2-1.) Disassemble nose landing gear strut assembly in order of index numbers assigned to figure 2-1, with the following exceptions and special instructions:

d. If any bolt or pin is frozen in place and cannot be removed by application of moderate force, bolt or pin is to be drilled out. Bolt or pin is to be drilled along its centerline and drill size used is not to exceed frozen bolt or pin OD minus 0.030 inch. Shell of bolt or pin remaining in hole is to be broken out or pressed out. NOTE

Plug (76) need not be removed when disassembling the shock strut. See subparagraph 2-4.a.(6).

Do not loosen or remove valve body or valve core to exhaust air pressure. Unless all pressure is released before removal of valve body or valve core, these parts may be blown out with great force and may cause bodily injury. a. Before disassembling strut, remove valve cap and loosen hexagon swivel nut of valve, part No. AN6287-1, one-half to one turn. Depress valve core until air pressure is released; then unscrew and remove valve body. NOTE

It is recommended that hydraulic fluid drained from strut be filtered so that any foreign matter found in fluid may help to identify source of any trouble. b. Drain all hydraulic fluid by removing plug (4). Move piston through its stroke a few times to aid in ejecting all fluid. c. Use wrench assembly, part No. 404224-1, to remove seal retainer (57) and screwdriver, part No. 755116, to remove screws (541, part No. NAS517-3, from nut plate (56).

23.

CLEANING.

Provide adequate ventilation when using dry cleaning solvent. Avoid skin and eye contact. Do not use near flame, spark or other source of ignition. Compressed air must be limited to a maximum of 30 psi when used for cleaning andfor drying operations; also, eye protection must be worn to prevent eye injuries. a. Clean all metal parts with solvent, Federal Specification P-D-680. b. After cleaning, dry all parts with compressed air. Coat with hydraulic fluid, specification MIL-H-5606 or MILH-83282, all parts that come in contact with fluid during operation of strut. c. Wipe thermosetting plastic parts clean with a cloth dampened with hydraulic fluid, Specification MILH-5606 or MIL-H-83282. d. Do not clean packings, backup rings, valve core, wipers, and scraper rings as they are all to be replaced at each overhaul.

T.O. 4S2-23-3

i'Yq Do not attempt to cut or scrape sealant from steering collar area. Catastrophic stress risers on outer cylinder could result in the form of cuts, gouges, and scratches. e. Remove sealant, Specification MILS-81733, from steering collar area, with solvent, Specification MIL-D-9063. 2-4.

INSPECTION, REPAIR, AND REPLACEMENT.

All shotpeening, grinding, and abrasive blasting operations must be performed in an adequately ventilated booth. Local Bioenvironmental Engineer will provide information regarding specific respiratory and personal protective equipment requirements. a. Inspect all component parts of strut per applicable directives and overhaul criteria outlined herein: (1) Make a thorough inspection of cylinder (181, piston axle assembly (251, and firlcrum assembly (14) for any evidence of scratches, galls, scores or corrosion.

Provide adequate ventilation during f luorescent-penetrant inspection. Wear protective gloves and prevent skin contact with solution and developer. (21 Perform a magnetic-particle inspection (magnaflux) for cracks and flaws in all ferrous parts per Specification MILI-6868 or section IV as applicable. (3) Inspect all holes and bushings for quality and taper using appropriate instruments. (See allowable service dimensions, table 2-2.) (4) Inspect all internal and external screw threads for evidence of scoring or stripping. Replace any part that is found to have unserviceable screw threads.

(5) Carry out a thorough inspection of fulcrum (14, figure 2-11, side struts (131, collar (681, sleeve (711, and other components. (6) It is not necessary to remove plug assembly (76) from outer cylinder (18) unless inspection shows indication of damage. If there is indication of damage, remove plug for inspection of mating surfaces of plug and cylinder. NOTE

Identify each assembly with cylinder from which it is removed so that original alignment will be maintained at reassembly. (7) Inspect and repair all parts in accordance with table 2-3. b. The overhaul criteria below will apply to specific procedures called out in repair instructions that follow: ( 1) Grind. Accomplish per MIL-STD-866.

All grinding operations shall be followed by nital etch inspection for burns or cracks. Nital etch inspection must be accoml plished by qualified p e r s o ~ eonly. (21 Nital Etch Inspection. Accomplish per MIL-STD-867. (3) Bake. Bake for four hours at 375 (+25I0Fwithin four hours after grinding. Bake for 23 hours at 375 (f25)QF within four hours after plating. NOTE

Rework (grinding and plating) of more than one specific area on a major subassembly may be accomplished concurrently, provided time limitations prior to baking are Willed. (4) Shotpeen. Use No. S-230 steel or stainless steel shot at 0.010 to 0.012 inch A2 intensity per Specification MIL-S-13165. ( 5 ) Polishing. (a) Accomplish per MIL-STD-866. Use 320-grit or finer crocus cloth, by hand or roll mandrel in a rotary drill motor, to polish corrosion or tool marks from surfaces.

T.O. 4S2-233

Legend 1 . LOCKWIRE

27. 28. 29. 30. 31. 32. 33. 34. 35. 36. 37. 38. 39. 40. 41. 42. 43. 44. 45. 46. 47. 48. 49. 50. 51.

2. VALVE 3. O-RING PACKING 4. DRAIN PLUG 5. GASKET 6. PIN 7. BUSHING 8. NUT 9. WASHER 10. WASHER il. WASHER 12. BOLT 13. STRUT ASSEMBLY 14. FULCRUM ASSEMBLY 15. PLUG 16. DRIVE SCREW 17. KEY 18. CYLINDER ASSEMBLY 19. BUSHING 20. FllllNG 21. BUSHING 22. LOCKWIRE 23. SCREW 24. GLAND NUT ( W E N ) 25. PISTON ASSEMBLY 26. COlTER PIN

PIN RETAINER BEARING RETAINER PIN CAM CAM KEY KEY CONE BEARING WAVE WASHER ADAPTER BACKUP RlNG O-RING PACKING O-RING PACKING BACKUP RlNG ADAPTER SCRAPER FELT BUSHING NUT WASHER RETAINER BULKHEAD

O-RING PACKING BACKUP RlNG SCREW ORIFICE ASSEMBLY NUT PLATE 57. SEAL RETAINER 58. O-RING PACKING 59. BACKUP RlNG 60. O-RING PACKING 61. BACKUP RlNG 62. LOCKWIRE 63. S C R W 64. NUT 65. BRACKET ASSEMBLY 66. KEY 67. FIlTlNG 68. COLLAR ASSEMBLY 69. RlTlNG 70. BUSHING 71. SLEEVE 72. TAG 73. NAMEPLATE 74. NAMEPLATE 75. NAMEPLATE 76. UPPER CYLINDER PLUG

52. 53. 54. 55. 58.

Figure 2-1. Nose L a d i n g Gear Strut Assembly (Sheet 2 of 2) Table 2-2. Replacement and Reconditioning Dimensions

(SEE

ORIGINAL ROUNDNESS, CLEARANCE ALLOWABLE CONCENTRICITY, BETWEEN SERVICE PARALLELISM DIMENSIONS PARTS

INDEX NO.

PART NAME LOCALITY OF DIMENSION

14

Fulcrum Heyway

0.376 0.375

GY

0.374 0.373

Cylinder Outer Sleeve Attaching Bushing P i . Attaching Hole TOPLugs Cylinder Be-g Surface

5.2498 OD 5.2484

0.003

max

1.4375 ID 1.4392

0.003

min max

FIGURE 2-1)

(width) 17 18

19

Bushing

ORIGINAL DIMENSION

4.440 4.443

max min

max min

ID

1.8755 ID 1.8765

min 0.003

max min

'

0.003 0.001

0.380

0.003 0.001

0.3725

0.0030 0.0002

5.2460 OD

0.0049 0.0015

1.4420 ID

0.008 0.003

4.450

ID

1.8780 ID

-

T.O. 4S2-23-3

Figure 2-1. Nose W i n g Gear Strut Assembly (Sheet 1 of 2)

Change 1 23

T.O. 482-233

Table 2-2. Replacement and Reconditioning Dimensions (Cont)

(SEE FIGURE 2-1) INDEX NO. 21

PART NAME LOCALITY OF DIMENSION Bushing Bushing - Faceto-Face for Cylinder, part Nos. 7926628 and 357370 Bushing - Faceto-Face for Cylinder, part No. 371675

25

29

ORIGINAL DIMENSION 1.0019ID 1.0000 0.93310.043

ORIGINAL CLEARANCE ALLOWABLE ROUNDNESS, CONCENTRICITY, BETWEEN SERVICE PARAILELISM PARTS DIMENSIONS 0.003 max 0.0037 1.0030 ID min 0.0008

1.22131 1.0023

Piston before plating Piston after plating

3.9913 OD 3.9891 3.9975 OD 3.9953

Bearing

4.437 OD 4.435

0.002TIR (total indicator reading)

min

0.003 TIR

max

max

min

0.0077 3.993 0.0025 0.008 4.432 OD 0.003

Key

0.188 0.187

max min

0.003 0.1865 0.001

35

Key

0.375 0.373

max min

0.003 0.372 0.001

37

Bearing

4.003ID 4.000

0.003 TIR

34

min

0.0077 4.006 ID 0.0025

max

39

Adapter

4.0022 ID 4.0002

0.003TIR

max min

0.0069 4.0048 ID 0.0025

44

Adapter

4.0022 ID 4.0000

0.003TIR

max min

0.0069 4.0048 ID 0.0025

47

Bushing

1.1260ID 1.1250

0.006

max

0.0020 1.1270ID 0.0002

1.37451 1.3750

NA

65

Bracket (holes), part No. 355845-1 Part No. 352607

1.43701 1.4378

min

max

0.0025 1.3760 0.001 interference 1.4388

min

T.O. 4S2-23-3

Table 2-2. Replocement and Reconditioning Dimensions (Cont)

(SEE PART NAME FIGURE LOCALITY OF 2-1) DIMENSION INDEX NO. 66 Key 68

Collar Collar (2holes)

70 71

Bushing Sleeve Sleeve

ORIGINAL DIMENSION 0.5010 0.4995

ORIGINAL CLEARANCE ALLOWABLE ROUNDNESS, CONCENTRICITY, BETWEEN SERVICE PARTS PARALLELISM DIMENSIONS max 0.0025 0.4990 min (-1 0.001

5.5014 ID 5.5000 1.3750 1.3760

max

1.1260ID 1.1250

max

5.2500 ID 5.2514 5.4974 OD 5.4956

min

max min min

Thickness Thickness Of section of w a ~ . 0.1278/0.1210inch. Flange thickness 0.170/0.145inch.

max min max min

0.0057 5.5035ID 0.0026 0.0008 1.3770ID 0.0002 0.0020 1.1270ID 0.0002 0.0030 5.2528 0.0002 0.0057 5.4942 0.0026

Table 2-3. Repair and Rework SERVICE (WEAR)

REPAIR DIMENSIONS (SEE FIGURE 2-1) LOCATION OR INDEX NO.

ORIGINAL DIMENSIONS

REWORK LIMITS

MAX

MAX

MACH FINISH

HOLE OVERSIZE

MIN

MAX

MIN

MAX

MIN

MAX

ANCE

REPLACEMENT PART

Outer Cylinder Drag Pin Hole

1.4375

1.4392

0.0015

0.0049

---

1.440

0.008

68C29134-01

63

ID

ID

Drag Pin Bushing (7)

1.4343 OD

1.4360 OD

0.0015

0.0049

1.4320

---

0.008

68C29134-01

Drag Pin Bushing (7)

1.2500

1.2510

0.0002

0.002

-----

1.253

0.006

ID

ID

Drag Pin (6)

1.2490 OD

1.2498 OD

0.0002

0.002

1.247

----

Side Brace Bolt Holes (14) (18)

0.7500

0.7509

-----

----

----

ID

JD

Side Brace (13) (Strut Assembly)

0.7500

0.7509

-----

----

ID

ID

Actuator Attach Holes (18)

1.1875

1.1885

-----

ID

ID

Bushing (21)

1.1890 OD

1.1898 OD

Bushing (21)

1.0000

1.0019

ID

ID

1.3750

1.3760

ID

ID

Bushing (70)

1.3765 OD

1.3773 OD

Bushing (70)

1.125

1.126

ID

ID

1.3750

1.3760

ID

ID

Bushing (47)

1.3765 OD

1.3773 OD

Bushing (47)

1.125

1.126

T.A. Attach Lug (68)

T . k Lug (25)

Steering Cylinder Attach Holes (18)

ID

m

2.000

2.0011 OD

ID

CLEARANCE

DIAMETER

CLEAR-

BUSHING INTERFERENCE MIN

MAX

1.5562

0.0002 LOOSE

0.003 LOOSE

100

-----

-----

-----

63C29134-01

160

-----

-----

-----

0.006

-----------

100

-----

-----

-----

0.753

0.0045

68D29135-35

63

0.8704

0.0006

0.0015

----

0.753

0.0045

68D29135-47

63

0.804

0.0006

0.0015

----

----

----

-----

68D29135-41

63

1.3063

0.0007

0.0015

-----

----

----

----

-----

68D29135-41

125

-----

-----

-----

0.0008

0.0037

----

1.004

0.0065

68D29135-41

125

-----

-----

-----

-----

----

----

----

--..-

68D29135-53

63

1.4993

0.0007

0.0014

-----

.--- .--- ----

-----

68D29135-53

125

-----

-----

-----

----

0.005

68D29135-53

125

-----

-----

-----

---.

-----

68D29135-83

63

1.4993

0.0007

0.002

.-.-

-----

681329135-83

125

-----

-----

-*---

0.006

68D29135-83

125

-----

-----

-----

68D29135-39

63

2.199

0.001

0.0027

0.0002

0.002

-----

...-

-----

----

0.0002

0.002

--em

...----

1.128

1.129

T.O. 4S2-23-3

NOTE

Do not use dry grinding stones or wheels. Prevent surface temperatures above 400°F' by rapid and continuous movement of the polishing tool. (b) If corrosion pits are deep, employ hand files to remove major portion of defects and finish removal with polishing method above. (6) All chrome plating referenced in this manual shall be accomplished in accordance with MIL-STD-1501,Type I., Class 3.

Provide adequate ventilation during cadmium plating. Wear protective gloves and chemical goggledface shield to prevent skin and eye contact. Local Bioenvironmental Engineer will provide information regarding specific respiratory and personal protective equipment requirements. (7) Vacuum cadmium plate areas noted in figures 2-2,2-3, and 2-4 and table 2-4 per Specification MIL-C-8837, Type 11, 0.0003 inch minimum thickness, except 0.0003 inch maximum thickness on threads and splines. c. Outer cylinders (25) corroded to extent that corrosion c a ~ o be t removed within service wear limits specified in table 2-2. Rework in accordance with the following criteria: Table 2-4. Vacuum Cadmium Plate Areas

(See figure 2-1) PART DESCRIPTION

AREAS TO PLAlE Entire outer surface Strut Assembly (13) and end hole ID. All over, except where Steering Collar chrome plated. Assembly (76) All over, except ID if Steering Cylinder Bracket Assembly (73) it is chrome plated.

Vacuum cadmium plate all external surfaces not chrome plated including lugs, lug ID, steering flanges, and bearing areas (figure 2-2). (1) Lower Bearing Area: NOTE

OD of lower bore may have 0.010 inch material removed to true up and made OD concentric with ID to eliminate excessive setup time. Reworked area will have a minimum 114 inch transition radius. Break sharp edges. Shotpeen reworked area per Specification MIL-S-13165, 0.008 to 0.012A2 intensity, 100 percent coverage, 0.023 to 0.028 diameter steel shot. (a) Remove isolated corrosion by locally grinding or polishing, but not to exceed 0.020 inch below minimum blueprint tolerance, provided isolated corrosion does not extend into bearing seal area. Local grinding will be limited to 20 percent of surface area. (b) Remove more extensive corrosion from lower bearing area by boring, honing or grinding bore oversize not to exceed 0.020 inch over drawing dimensions. Maintain a surface roughness of 32 RMS maximum.

-1 Bake.

-2

Shotpeen.

3 Mask inside diameter of cylinder, inside diam2ter of fillet radius threads, and other surfaces that would be affected by plating runout or fume concentrations. 4 Chrome plate per MIGSTD-1501, Type 11, Class 3.

-5 Bake. 6 Grind and chamfer to drawing specification. R& out plating from maximum on inside of bearing bore between 0.020 inch and 0.050 inch from outboard intersection of internal chamfer.

-7 Bake.

T.O. 4S2-233

........... ...........

LEGEND CHROMIUM PLATE VACUUM CADIMUM PLATE I F CHROMIUM PLATE IS NOT RE QUIRED,VACUUM CADIMUM PLATE

G9100732

Figure 2-2. Plating of Nose Landing Gear Outer Cylinder

T.O. 4S2-23-3

LEGEND A . CHROMIUM PLATE B VACUUM CADMIUM PLATE C . IF CHROMIUM PLATING IS NOT REQUIRED, VACUUM CADMIUM PLATE

.

G9 100733

Figux 2-3. Pluting of Nose Landing Gear Piston

LEGEND

k

A. CHROMIUM PLATE

.

B VACUUM CADMIUM PLATE C . IF CHROMIUM PLATING IS NOT REQUIRED, VACUUM CADMIUM

PLATE

T.O. 4S2-233

(2) InternalSurfaceofAir Chamber: (a) Rework internal diameter to a 64 RMS maximum surface finish. Do not exceed a maximum inside diameter of 5.020 inches. Polish 0.38 inch radius surfaces. (b) Bake. (c) Shotpeen internal surface including radius. (dl Magnetic-particle inspect per Specification MIL-1-6868.

(b) Outer cylinder, part No. 357370-. 1 Remove defects from fulcrum attaching aiba by locally grinding or polishing to a depth of 0.020 inch below drawing minimum wall thickness but not to exceed 20 percent of surface area. Machine or grind more extensive corrosion to a maximum depth of 0.010 inch; material removed on the radius not to exceed 3.9786-inch minimum diameter. Process per MIL-STD-866.

2 Shotpeen. -

(3) Cylinder Inside Diameter, Upper Plug Assembly Mating Surface:

3 Mask inside diameter of cylinder, all external hoGs, and radii to prevent plating runout in the areas.

(a) Remove corrosion by locally polishing or grinding to a maximum depth of 0.020 inch but not in excess of 20 percent of surface area.

4 Chmme plate per MTL-STD-1501, Type 11, ClGs 3.

(b) If corrosion exceeds 20 percent of surface area, grind bore oversize sufficient to remove defects to a maximum depth of 0.020 inch on diameter.

5 Grind to finish drawing dimensions. Run out pl3,ing from maximum thickness to zero thickness, 0.040 to 0.020 inch, respectively, outside radius tangent points on area being plated. Grind per MIL-STD-866.

(c) Bake.

(dl Shotpeen. (el Chrome plate per MIL-STD-1501, Type 11, Class 3. (fl

Bake.

(g) Grind to drawing specifications.

-6 Material removal in keyways is not

allowed.

(c)

1 Remove defects from fulcrum attaching &ea OD by grinding, not to exceed a minimum of 4.474 inches diameter. Grind per MILSTD-866.

(h) Bake. (4) Outer Surface Corrosion of Cylinder: (a) Outer cylinder, part Nos. 357370and 371675-. 1 Remove superficial corrosion by abrasive blast cleaning with aluminum oxide, 180 mesh or finer, except steering collar area. NOTE

All cylinder surfaces shall be shotpeened to an 0.010 to 0.012A2 intensity per Specification MIL-S-13165 using No. 230 or 280 steel shot except threads and upper ID 25.0 inches from lower end of outer cylinder. 2 Grind shoulder and radius on fulcrum beariZg surface (below fulcrum) to a maximum of 0.030 inch material removal. Maintain drawing radius tolerances. Process per MPSTD866.

-3 Shotpeen.

Outer cylinder, part No. 371675-.

-2 Shotpeen. 3

1501, Type

Chrome plate OD per MIL-STD-

n,Class 3.

4 Grind OD of fidcrum attaching area to drawing finish dimensions per MIL-STD-866. 5 Corrosion pits to a depth of 0.0301 0.040 max&um in fulcrum attaching keyways may be reworked by abrasive grit blasting to remove corrosion products. 6 Cadmium plate grit blasted area per MIL-STD-870, Type 11, or vacuum cadmium plate per Specification MIL-C-8837, Q p e II. It is not necessary to machindgrind area to remove pits. (5) Steering Collar Mating Surface on Outside Diameter of Outer Cylinder. (a) Grind or polish defects to minimum depths required for corrosion removal within rework dimensions shown in table 2-5 for respective areas, but not to exceed specified minimum wall thickness unless otherwise specified.

T.O. 4S2-233

Table 2-5. Rework Criteria

STEERING COLLAR MATING SURFACE ON THE OUTSIDE DIAMETER OF THE OUTER CYLINDER

A. Strut, Part Nos. 363590-lA, -5, -7, and 364653-2A

1. Upper Radius Area (above

2. 3. 4.

5. 6.

upper bearing land) Flange Face Area (between bearing lands) Lower Radius Area (below lower bearing land) Raised Bearing Land Nut Retaining Keyways (4 each) Sleeve Bracket Keyways (2 each)

PRESENT DIMENSIONS

REWORK DIMENSIONS

5.000-inch diameter

4.930-inch diameter minimum with 0.2435-inch minimum wall 4.862-inch diameter minimum with 0.2095-inch minimum wall 5.07-inch diameter minimum with 0.314-inch minimum wall Grind to 5.2298 inches minimum 0.2585-inch minimum wall

4.902-inch diameter 5.13-inch diameter 5.2484l5.2498-inch diameter

0.125-inch minimum wall

B. Strut, Part Nos. 361671-1, 388071-1, -3, -5, -9, 3401095-11, and 7926829-10. 1. Upper Radius Area (above

5.100-inch diameter

upper bearing land) 2. Flange Face Area (between bearing lands)

5.002-inch diameter

3. Lower Radius Area (below lower bearing land) 4. Raised Bearing Land 5. Nut Retaining Keyways (4 each) 6. Sleeve Bracket Keyways (2 each)

5.13-inch diameter 5.2484.6.2498-inch diameter

1 If isolated pits are present in upper radius abovz top bearing land which will polish out without grinding entire area, locally polish not to exceed specified minimum wall dimensions and blend into surrounding area. 2 Locally polish corrosion from four small nut rexainer keyways not to exceed 0.020 inch depth into cylinder wall section. Locally polish entire width not to exceed 0.214 inch (0.013 inch each side). 3 Locally polish two steering bracket retainer keyways to 0.010 inch depth not to exceed

5.070-inch diameter minimum with 0.3135-inch minimum wall Spot rework to 0.030-inch depth over 20 percent of area or circumference to 0.2495-inch minimum wall 5.09-inch diameter minimum with 0.3235-inch minimum wall Grind to 5.2298 inches minimum 0.2585-inch minimum wall 0.135-inch minimum wall (20 percent of surface area maximum)

20 percent of surface area. Locally grindlpolish entire width not to exceed 0.535 inch (0.017 inch1 side). Keys that fit into sleeve bracket will have to be manufactured from 4340 steel bar (H.T. 180000/ 200000) for each specific keyway to give a clearance of 0.000/0.0035 inch. Manufacture width of keys to dimension that outer cylinder keyway slots have been reworked to, with a height of 0.20010.210 inch (oversize width of a key is not to protrude above outer cylinder surface). Remainder of key is to be same dimension as a standard key. Where key transitions from a wide base to standard dimensions, there should be a 1/32 inch radius.

T.O. 482-23-3 NOTE

All polishing shall be accomplished so that polishing marks are on longitudinal axis of outer cylinder. 4 Additional rework for outer cylinders, part Kos. 371675- and 3303589- only: a Grind entire width of two steering bracket reE'er keyways not to exceed 0.550 (0.025/side). Depth of material removal in keyway is limited such that remaining cylinder wall thickness is 0.130 inch minimum. Keys that fit into sleeve bracket will have to be manufactured per subparagraph 3 above. (b) Raised bearing lands which are corroded may be ground as necessary to remove corrosion, but not to exceed 5.2298 inches minimum outside diameter. Spot corrosion may be removed to a depth of 0.050 inch maximum over 20 percent of flat surface. No area of spot rework on lands shall be greater than one square inch. No two areas shall be closer than one-half inch apart. Blend all rework areas with a 1.00 inch radius. Edges of all reworked areas will be blended into adjacent area. (c) Bake. (d) Shotpeen.

(e) Mask all radius areas and keyways. (0 Chrome plate bearing land flats and grind to finish dimension. Feather all plating between 0.030 to 0.010 inch fmm maximum to zero thickness fkom intersection of radius and tangent on both sides of plated surface. ( g ) Bake. (h) Grind to finish dimension, 5.24981 5.2484 inches.

(i) Bake.

6) Vacuum cadmium plate remaining area in conjunction with outer cylinder exterior surface.

a WARNING

Trichloroethane vapors are extremely hazardous if inhaled in high concentration. Wear an organic type respirator to avoid inhalation effects if vapors are identified by smell. Rubber gloves should be worn to avoid skin contact. Use only in well-ventilated area. (k) After plating, clean surface thoroughly with trichloroethane, Federal Specification 0-T-620. Pack area fill and completely with grease, Specification MPG-81322. (1) If no more than 20 percent of chrome surface is pitted, replating is not required. These areas should be blended, width of rework being ten times the depth. No area of rework shall be more than 0.020 inch deep or cover more than 0.5 square inch of area. In addition, no two areas of rework shall be closer than one inch. If above conditions cannot be met, bearing lands must be replated. ( 6 ) Lugs on Outer Cylinder:

(a) Extend side brace lug service wear limit to 0.752 inch maximum inside diameter. (b) Remove corrosion that cannot be removed within service limit of above by honing or line reaming to 0.830010.8309 inch.

T.O. 4S2-233

(c) Manufacture bushing from 4330 steel, heat treated to 220,0001240,000 psi per Specification MIL-H-6875. Dimensions: OD 0.831910.8320 inch ID 0.749010.7495 inch Finish ID: 0.7500 (+0.0051-0.000)inch Length: 0.250 (st0.010) Chamfer end: 0.030 x 45" (d) Apply wet sealant, Specification MIL-S-81733, and press bushing into place. (7) Nut, Steering Threads on Outside of Outer Cylinder: (a) Threads with minor surface corrosion may be reworked by glass bead blasting per MLSTD-1504. Thread root may be reworked to a depth of 0.005 maximum. Reworked major diameters will be as follows: 1 Steering collar mounting threads 5.2366 inch& minimum. -2 Cylinder lower threads - 5.1116 inches minimum. I (8) Steering Bracket (651, Part Nos. 352607 and 355845-1: (a) Grind inside diameter for steering bracket to remove corrosion but not to exceed 5.272 inches. Locally polish isolated pits as required up to 0.040 inch depth maximum not to exceed 30 percent of circumference. Remove corrosion on flat surfaces by locally polishing or air blasting with aluminum oxide grit or suitable substitute until corrosion products are removed. Corrosion removal shall be limited to 45 percent of surface area and 0.030 inch maximum depth. Chrome plate ID and grind to 5.25015.252 inches in accordance with MIL-STD1501, Type 11, Class 3, and MIL-STD-866. Sulfamate nickel plating per MIL-STD-868 may be used as an alternate method. (b) Remove corrosion from plane surfaces of steering bracket arms (areas adjacent to 5.250 bore) by locally polishing not in excess of 0.020 inch depth, not to exceed more than 30 percent of either surface. If corrosion is over entire surface area, grind either or both surfaces 0.010 inch maximum. The 0.500 inch thickness will not be reduced below 0.480 inch during grinding. Grind per MIL-STD-866 to 250 RMS or better surface finish. If corrosion exists after grinding, but is less than 0.010 inch depth for 30 percent of surface, remove by local polishing. Corrosion in excess of above repair will be cause for replacement. -1 Bake at 375 (k25)OFfor four hours.

2 Shotpeen in accordance with Specification m-S-13165. 3 Vacuum cadmium plate in accordance with- Specification MIL-C-8837, Type 11, 0.0003 inch minimum thickness. (c) (Part No. 355845-1 only.) Corrosion and other defects on ID of 1.374511.3750-inch steering cylinder hole may be removed to an ID of 1.5993 inches. The 1.170-inch diameter opening at bottom of this hole should not be enlarged. Walls of reworked portion of hole should be blended with bottom of hole using 0.01010.030 inch fillet radius. The chamfer of OD of 68D29135-49 bushing shall be increased to 45 degrees x 0.03010.035 inch. (9) Steering Collar (68), Part No. 352604: .I (a) Remove corrosion from inside diameter by locally polishing or grinding sufficiently to remove defects but not to exceed 0.030 inch in depth or 35 percent of surface area. Maintain a finish of 32 RMS surface roughness with a minimum radius of 0.500 inch blending reworked area into parent metal. 1 Shotpeen reworked surface. Fade shotpeeninfin surfaces adjacent to reworked areas. 2 Bake as per subparagraph 2-4b.(3). (b) If corrosion cannot be removed in accordance with subparagraph (a), grind ID oversize 0.030 inch. 1 Isolated pits remaining after grind shall be removed by locally polishing at a depth of 0.020 inch. 2 Shotpeen ID. -3 Bake as per subparagraph 2-4.b.(3). 4 Chrome plate inside diameter of collar per MPSTD-1501, Type II,Class 3. -5 Grind ID to 5.5000/5.5014 inches. -6 Bake as per subparagraph 2-4.b.(3). (c) If corrosion still remains after grinding ID at 5.530 inches, grind ID to maximum of 5.540 inches for flame spray repair per MTL-STD868 using METCO 451 material. Sulfamate nickel plating per MTL-STD-868 may be used as an alternate method. Finish grinding ID to final dimension of 5.500015.5014 inches. -1 Bake for four hours at 375 (e5)OF. 2 Chrome plate either or both surfaces as required and grind to drawing dimensions. Chrome plate is in accordance with MTL-STD-1501, Type 11, Class 3.

Change 1 2-15

T.O. 4S2-23-3

-3

Bake for four hours a t 375 (e5)OF.

Remove surfaces of steering collar (areas adjacent to 5.5000 inch bore) by locally polishing, but not to exceed 0.020 inch d e ~ t h . Do not exceed more than 20 percent of eicher surface. Grind either or both surfaces 0.020 inch maximum per MPSTD-866. Chrome plate either or both surfaces as required and finish grinding to final dimension of 2.7481 2.750 inches. (10) Steering collar sleeves (71, figure 2-11 which are worn such that they are no longer within print tolerances, may be machined to bring them back to size provided they meet all print dimensions after rework. (11) Pulley Mounting Lugs: (a) A bent lug may be straightened by applying sufficient force to lug to restore it to its proper position. Shotpeen affected areas 0.0101

0.014 inch A* intensity per Specification MIL-S13165. ~ake-fourho& -at 375 (lt25)OF and magnetic-particle inspect per T.O. 33B-1-1 for crack appear, repair in accordance indications. If with subpsragaph (b). (b) Broken and cracked lugs shall be repaired by boring broken lugs (left or right) on centerline of attached lug as shown in figure 2-5. Counterbore bottom 0.100 inch deep as shown in figure 2-5. Ream and hone as noted to establish fGal inside diameter (0.89710.898) of hole as shown. Shotpeen hole inside diameter surfaces 0.01010.014 inch A2 intensity per Specification MILS-13165. Magnetic-particle inspect for cracks per T.O. 33B-1-1. Apply wet sealant, Specification MIL-S81733, to inside diameter and press bushing, part No. 68D29135-91, into place. Machine top portion of bushing to conform to contour shown in figure 2-5. Drill and ream 0.250010.2508 inch hole as shown. DIA.

HCNE TO FINISH I.D. ,

0.002/0.003 AFTER REAMING

REAM TO REFINISH I.D. 0.003/0.0045 REMOVAL AFTER BORING OPERATION

DRILL 8 LINE' REAM 0.2500/ 0.2508 DIA

a loo Figure 2-5. Pulley Mounting Lugs Repair

0.450 R

T.O. 4S2-23-3

d.

Plug Assembly (76, figure 2-1).

(1) Extend service wear limits of pin boss inside diameter to 1.441 inches.

(a) If corrosion cannot be removed within above wear limits, bore or ream boss oversize 1.465011.4675 inches for installation of oversize bushings. (2) Plug Surface:

Assembly,

Cylinder

Mating

(a) Locally polish or grind isolated corrosion not to exceed a depth of 0.020 inch and not to exceed more than 20 percent of surface areas. This does not apply to sealing surfaces. (b) If corrosion exceeds 20 percent of surface area, grind outer surface areas sufficiently to remove corrosion but not to exceed 0.020 inch in diameter. (c)

Bake.

(d) Shotpeen. (el Chrome plate outside diameter of cylinder mating surface per MILSTD-1501, Type II, Class 3. (f)

Bake.

(g) Grind to drawing dimensions.

drawing specification. All notes and concentricities will control rework limits. (3) Upper piston head bearing areas OD and ID. Rework part Nos. 340877, 355400, and 388028. (a) Grind corrosion from upper piston head OD as required, not to exceed 3.7878 inches minimum and ID to 3.500 inches maximum. Wall material thickness of 0.1439 inch minimum after final grind, before plating, must be maintained or part will be condemned. Shotpeen, chromeplate OD per MIL-STD-1501, Type 11,Class 3. Grind back to drawing finish dimension of 3.810013.8078 inches.

Provide adequate ventilation during f luorescent-penetrant inspection. Wear protective gloves and prevent skin contact with solution and developer. (4) Magnetic-particle inspect 0.50-inch radius below piston chrome in accordance with section IV.

(a) If cracks are not found, polish radius and relief.

(h) Bake. (3) Actuator lug bushings (21) should have the following face-to-face dimensions when installed: (a) Cylinder, part Nos. 7926628 and 357370: 0.93310.943 face-to-face. (b) Cylinder, part No. 371675: 1.00131 1.0023 face. e.

PistonlAxle Assembly (25): (1) Vacuum cadmium plate all external

surfaces not chrome plated including lugs, lug ID, and bearing areas. Plating on ID of piston is optional (figure 2-31. Plate ID of axle. Apply corrosion-preventive coating, Specification MIL-C27725B, Type I . , Class A, over cadmium plate on ID of the axle only. (2) Local polish minor blemishes within wear tolerance of table 2-2. If plated surface of piston is worn beyond tolerance or damaged by corrosion, recondition surface by grinding sufficiently to remove defects but not to exceed a minimum diameter of 3.9825 inches. A minimum wall thickness of 0.171 inch shall be maintained after final grind before plating. Replace and grind to

Nital etch inspection must be accoml plished by qualified p e r s o ~ eonly. (b) Nital etch inspect. (c) If defects are not found, shotpeen and apply a film of compound, Specification =-I8660. (dl If defects are found, hand file or polish sufficiently to remove defects, but not to a wall thickness less than 0.155 inch. (Allow for eccentricity between inner and outer diameters when determining wall thickness.) Inspect frequently to ensure a minimum amount of material removal. Maintain a 32 RMS finish and a 0.50 to 1.00 inch radius. It may be necessary to remove some of the chromium plating that extends into affected area. (el Bake.

(fl Nital etch inspect. (g)

Shotpeen.

(h) Bake.

T.O. 4S2-23-3

( 5 ) Inspect wheel bearing journals of axle for wear, scoring, galls, and pits.

(a) On outer bearing journals, minor blemishes may be locally polished provided: 1 No more than 20 percent of bearing area is affec-ted by polishing.

2 Depth of polishing does not exceed

0.003 inch.

-

3 No more than 30 percent of any one square inch-of area is affected by polishing. (b) On inner bearing journals, minor blemishes may be locally polished provided: 1 No more than 20 percent of bearing area is affe&d by polishing to a depth not to exceed 0.003 inch.

radius.

-2

No pit edge is sharper than 0.060

3 No more than 30 percent of any one square inch-of area is affected by polishing. (c)

If damage is more extensive:

1 Grind outer journals sufficiently to remove defgcts not to exceed 0.015 inch material removal on diameter.

2 Grind each inner journal to a . OD sufficient 6 remove defects, but not less than 2.9830 inches nor greater than 2.9950 inches. If defects remain, they may be further reworked by local hand polishing over not more than two square inches total area on each journal, such that no single area of polishing is larger than one square inch and such that no two areas of polishing are within one inch of each other. Blend polished areas smoothly with surrounding areas. M i a h u m allowable wall thickness after polishing is 0.510 inch for pistonlaxle assembly, part No. 240877-605. -3 Bake. 4 Nital etch inspect. -

-5 -6 -7 -8

-9

Bake. Shotpeen. Chrome plate. Bake. Grind to drawing specifications.

10 Bake. (6) If 1.375011.3760-inch inside diameter surface of torque arm attaching lugs of piston is worn, scored or pitted, repair as follows:

NOTE

Pistons having torque arm attaching lugs less than 0.595 inch thick shall be condition condemned (do not include bushing flange in this dimension). (a) Line ream inside diameter of lugs to clean up bores but not to exceed 1.4993-inch ID. Maintain original 45 (e5I0 by 0.060 inch chamfer, both sides. (b) Install oversize bushings as specified in table 2-2. Line ream bushings to dimensional limits specified in table 2-2. Face bushing flanges to an outside dimension of 4.35014.348 inches. (c) Acceptable face-to-face dimension of inner bearing flanges is 12.010 to 11.880 inches.

(7) Corroded ID bulkhead seal may be repaired as follows: (a) Machine inner diameter as required to 3.016 mnm'murn. (b) Bake.

(c) Shotpeen. (dl Chrome plate sufficiently, to grind back to finish size. (el Bake.

(fl Grind and chamfer to drawing dimensions. (g) Fluorescent-penetrant inspect per Specification MIL-1-6866. f. Fulcrum Assembly (14, figure 2-11: (1) Vacuum cadmium plate all surfaces not chrome plated, including lugs, lug IDS, and bearing areas, except do not plate internal cavities of fulcrum assembly (figure 2-4).

(2) Bearing Journals: (a) Grind pitted, galled or scored fulcnun bearing journals sufficiently to remove defects, not less than 2.4210 inches (minimum diameter). (b) Shotpeen. (c) Mask areas adjacent to journals to ensure plating does not run out on radius and relief. (dl Chrome plate per MILSTD-1501, Type 11,Class 3, and grind to finish drawing dimensions and tolerances. (3) Bearing land area between threads and splines (0.585 inch width between threads and splines).

T.O. 4S2-23-3 (a) Grind corrosion from 1.874 OD to a minimum of 1.86211.864 OD. Shotpeen chromium plate in accordance with MIL-STD-1501 LHE,Type 11, Class 3, and grind to finish drawing dimensions and tolerances. Chromium plating thickness should not be less than 0.003 inch. Chromium plating crack inspection criteria shall be consistent with MIL-STD-1501, Type II, Class 3, except plated area shall be visually inspected under a white (oblique) light rather than dye-penetrant and black light.

,

(4). Cylinder attaching surface ID keyways, bottom face and top face, and runout area between ID and facings. Fulcrum, part Nos. 388072,371672, and 340872. (a) Cylinder attaching surface. 1 Rework by locally polishing to remove coGsion from ID, providing depth of pitting does not exceed 0.015 inch per wall and does not exceed 10 percent of surface area. If extensive rework is required, grind ID of fulcrum, part No. 388072-9, oversize to 4.516 inches or 4.020 inches for fulcrum, part No. 340872. Localized pitting remaining after tbis has been accomplished shall be removed by local polishing to above criteria. Shotpeen, chromium plate, and grind to finish drawing dimensions and tolerances per MILSTD-1501, Type II, Class 3. Chrome plate runout is allowable up to 114 inch from the edges of the keyways. (b) Keyways. 1 Remove corrosion to 0.010 inch depth by grass bead blasting in accordance with MIL-STD-1504. Shotpeen and vacuum cadmium plate. (c) Bottom and top faces and runout areas. 1 Grind corrosion from bottom and top faces not to-exceed minimum dimensions shown as A, figure 2-7. Maintain radius of runout areas not to exceed a minimum wall thickness (B,figure 2-71, either side of fulcrum. Shotpeen and vacuum cadmium plate reworked areas. (5) Threaded ends. (a) Cracks which extend from end of fulcrum into cotter pin holes need not be reworked. (b) Cracks which originate in cotter pin holes and extend towards center of fulcrum may be removed by blending the crack out. Use a 1/16 inch diameter cutter to blend out. Maximum material removal to blend out crack is 0.020 inch. (c) Cracks which originate at outboard end of fuicrum and extend towards the center will be removed by blending out. Use a 5/32 to 5/16 inch

diameter cutter to blend out. Maximum length of crack is 0.250 inch. (dl Remove only sufficient material to eliminate cracks. Maintain a 125 RMS or better surface finish. (el Limit of four cracks per end and only one crack per 90 degree quadrant, i.e., one crack between a pair of cotter pin holes. g. Steering Collar Sleeve (71, figure 2-1): (1) If not previously accomplished, rework keyway slot depth to 0.625 inch maximum to obtain a 0.090/0.110 inch radius in comers. (2) If cracks are evident in keyway comers and do not exceed 1/32 inch in depth, smooth and blend in with radius. (3) Cadmium plate ID and ends per MILSTD-870, Type II. h. Drill two holes 180 degrees apart, 0.387 inch above bottom face of gland nut (24). The hole size to be 0.1250 (+0.0015/-0.000) inch in diameter. Install fitting, part No. NAS-516-1, in each hole. i. Unless previously accomplished, modify wave washer (381, cone (361, and key (35) as follows: (1) Grind inside diameter of wave washer (381, part No. 360012-1, to 4.110 (f0.010) inches. (2) Increase inside diameter of cone (361, part No. 362142-1, to 4.110 (f0.010) inches. (3) Machine lip dimension of key (351, part NO. 355245-1, to 0.200 (7t0.005) inch. j. Keys, part No. MS20066-187, will have four edges chamfered 0.010/0.015 inch by 45 degrees and one end chamfered 1/16 inch by 45 degrees to aid in installation. Chamfer end mates with keyway in outer cylinder. k. Replace valve core with a new one (same type). Check O-ring of air valve assembly plug and bleeder to ensure a perfect seal during reassembly. 1. Corrosion is allowed on parts in areas not specifically addressed, but corrosion residue shall be removed by abrasive blasting. Reworked corrosion areas shall be neutralized. 2-5.

I I

LUBRICATION.

a. Before reassembly, immerse all internal packings, gaskets, and backup rings in hydraulic fluid, Specification MPH-5606 or MIL-H-83282. b. Lubricate pressure points and exterior mating surfaces with grease, Specification MIL-G81322.

Change 1 2-19

24. REASSEMBLY. (See figure 2-11, Reassembly in reverse order of disassembly, noting the following exceptions and instructions:

a. Replace all packings and backup rings as shown in figure 2-6. b. Before reassembly, immerse all internal packings, gaskets, and wiper rings in hydraulic fluid of the same type used in strut. c. Install seal retainer (57, figure 2-11, by placing cylinder assembly (18) on a bench at a slight angle with horizontal, with upper end higher than bottom end. Fit retainer on pins of the wrench, part No. 404224-1, and insert through bottom of cylinder. Slide guide, part No. 404226-1, ovek end of wrench shaft and fit into bore in cylinder bottom; then screw retainer into place and tighten it until 1-112 to 2 threads are visible below bottom of retainer. d. Install orifice assembly (59, by first inserting by hand the nut plate (56) through the 3-718-inch hole located inside cylinder approximately 24 inches above cylinder bottom. Hold nut plate flat on surface above hole and screw threaded end of holding rod, part No. 404225, into one of four nuts on nut plate. Place one orifice assembly mounting hole over free end of holding rod and slide orifice assembly into place against shoulder in cylinder.

The locator pin in orifice assembly must fit into slot in cylinder shoulder. Then use screwdriver, part No. 755116, to install two screws, part No. NAS517-6, (54) to connect orifice assembly to nut plate. Next, remove holding rod and install remaining two screws, part No. NAS517-6. e. Tighten gland nut (24) until lower bearing assembly (36, 37, 36) produces 3000 to 4000 inchpounds friction torque against rotation of piston (25). Check for proper torque by inserting a steel pipe through axle and attaching a spring scale to

protruding end. Pulling on spring scale, slowly turn piston axle to left or right. Note reading on spring scale required to turn axle. Multiply this reading by distance in inches measured firom the center between the axles to the scale attach point on the pipe. If reading is between 3000 to 4000 inchpounds, no further action is required. If this torque is not obtained, loosen the gland nut and repeat the procedure. Cycle the gear while making the adjustment to ensure proper seating of the parts. Alternate method for torquing gland nut: torque gland nut to 100 to 125 foot-pounds. f. When the cylinder is completely reassembled and tested, flush and drain with hydraulic fluid, Specification MIL-H-5606 or MIL-H-83282. Replace valve (2) and plug (4). g. Seal the thread joint, locking grooves, and unused locking screw holes of the gland nut (24) with sealing compound, Specification MILS-81733, Tgpe II. Seal the mating edges between the cylinder (181, plug (761, and fulcrum (14).

Provide adequate ventilation when using cleaning solvent. Avoid skin and eye contact. Do not use near flame, spark or other source of ignition.

h. Mask all areas not to be painted. Clean all surfaces to be painted by grit blasting with aluminum oxide, 180 mesh or finer, within four hours of painting. Immediately prior to painting, wash all items with acetone or naphtha, etc., and clean rags. i. Ensue that all blasting residue, grease, and fingerprints, etc., are removed.

j. Paint in accordance with applicable directives for high-strength steels and accomplish tape test after drying.

---

2-7. INSTAUATION OF BUSHINGS IN TOROUE -.ARMS. Bushing shall be installed in the upper -

-

- - -

andrower torque arms as shown in figure 2-8.

T.O. 4S2-233

NOSE STRUT

DON C-130A STRUTS WITH PLUG IN UPPER END.

Figure 2-6. Location of Seals

T.O. 4S2-233

PART NO. 340872

A 12.400 INCH MINIMUM B e 0.540 INCH MINIMUM PART NOS. 371672 AND 388072 A = 2.400 INCH MINIMUM B = 0.915 INCH MINIMUM C 12.860 INCH MAXIMUM (MAINTAIN RADIUSES AND ANGULAR REUTIONSHIP) D= 1.380 INCH W X I M U M (MAINTAIN RADIUSES AND ANGULAR RELATIONSHIP) (MATERIAL REMOVAL SAME ON BOTH SIDES)

Figure 2-7. Keyways

2-8.

REWORK FOR UPPER TORQUE ARMS.

Provide adequate ventilation during machining, sealing, and plating operations. The provisions of AFOSH Standards 161-1, 161-2, and 127-31 will be strictly adhered to regarding the adequacy of respiratory protection, ventilation, and personal protective clothing and equipment. a. Apex Lugs. Machine inside faces to remove wear marks. Remove 0.035-inch material maximum. Mixhum lug width after material removal to be 1.000 inch for part No. 380239-1 and 0.900 inch for part No. 355117-1. Maintain a 0.250-inch radius on inboard end of machine cut. Manufacture a flanged bushing as follows: (1) Material 4130 steel. Heat treated to 125 to 145 ksi. (2) Flange OD = 1.62011.600-inch diameter. (3) Flange width = 0.035 inch minimum. (4) Length of bushing = 112 width of reworked lug. (5) OD and ID = that of butting bushing. (6) Cadimum plate all over per MILSTD870, Type II, Class 2. Length of butting bushing will be cut down to l/2 width of reworked lug. Coat

OD of bushing with sealant, Specification MIL-S81733, and press bushing in place while sealant is damp. Wipe off excess sealant. Face-to-face dimension of rework lugs after bushing installation will be 1.62411.626 inches for part Nos. 355117-1 and 380239-1 and 1.40011.402 inches for part Nos. 388069-1 and 388069-5.

1

b. Base Lugs. Spot face with a mill machine outside faces to remove wear marks. Remove up to 0.035-inch material (minimum lug width after removal not to be less than 0.830 inch). Manufacture a flanged bushing (OD of flange not to extend out beyond torque arm lug OD; 1.78-inch OD typical, and bushing minimum thickness must be 0.030 inch) out of 4130 steel (heat treat 125 to 145 ksi) to replace regular bushing and bring outside dimension between lugs back to original drawing dimensions. Face-to-face dimension of bushings will be 1.62211.624 inches for part Nos. 355205-1 and 380240-1 and 1.39811.400 inches for part Nos. 388068-1 and 388068-5. 2-9. REWORK FOR LOWER TORQUE ARMS. a. Remove up to 0.035-inch material from inside face of lug &om original drawing dimension. Manufacture flange bushing. OD of flange to be within 0.030 inch OD of torque arm, but not protruding beyond OD of torque arm. Flange minimum wall thickness must be 0.030 inch. Bushing to be manufactured fiom same material as torque arm and with the same heat treat. Flange thickness to match material removed. 4340 steel acceptable substitute material.

Change 3 2-23

I

T.O. 42-233

UPPER TORQUE ARM, PART NO. 355117-1,3802341, 388089-1, AND 388069-5

UPPER TORQUE ARM, PART NO. 355117-1,3802341, 3880641, AND 3880694

LINE REAM BUSHING AFER INSTALLAnON

UNE REAM BUSHING A F E R INST"LLATI0N

LOWER TORQUE ARM PART NO. 3552051.380240-1, 388068-1, AND 388068-5

/

LOWER TORQLIE ARM PART NO. 355205-1,380240-1. 388066-1, AND 388088-5

Figue 2-8. Installation of Bushings in Torque Arms (Sheet 1 of 2)

2-24 Change 3

NOTE: 1.

ALL DIMENSIONS IN INCHES. MACHINE TO 1.40011.398 INCHES FOR PART NOS. 388068-1 AND -5 AND 1.62d1.622 INCHES FOR PART NOS. 380240-1 AND 355205-1 AFTER INSTALLATION OF BUSHINGS. CORRESPONDING DIMENSIONS FOR LOWER TORQUE ARM ASSEMBLIES USED IN OTHER STRUT ASSEMBLIES ARE SPECIFIED IN THE DIFFERENCE DATA SHEETS IN SECTION M.

PROVIDE ADEQUATE VENTILATION WHEN USING DRY ICE AND ALCOHOL. WEAR PROT E C m GLOVES AND PREVENT SKIN CONTACT. DO NOT INGEST. PRIOR TO BUSHING INSTALLATION, CLEAN PARTS AND BORE WITH ALIPHATIC NAPHTHA, FEDERAL SPECIFICATION 'IT-N-95, OR EQUIVALENT. APPLY THIN COAT OF CORROSION-PREVENTTVE COMPOUND, SPECIFICATION MILC-16173, GFtADE 1, TO ID OF HOUSING, AND WHILE STILL WET, SUBZERO INSTALL BUSHING USING DRY ICE AND ALCOHOL. CLEAN THE COUNTERSUNK AND CHAMFERED AREAS AND FILL WITH SEALANT, SPECIFICATION MILS-8802, AFTER INSTALLATION OF BUSHINGS. CLEAN AND APPLY BEAD OF SEALANT, SPECIFICATION MILS-8802, AFTER INSTALLATION OF BUSHINGS. Figure 2-8. Installation of Bushings in Torque Anns (Sheet 2 of 2)

Change 3 2-25/(2-26 blank)

T.O. 482-23-3

SECTION Ill TEST PROCEDURE 3-1. LEAKAGE TEST.

a. The purpose of the test is to ensure that there is no leakage past packing when strut - glands is serviced and extended: b. Test equipment used must be bottled air or nitrogen, and hydraulic fluid, Specification MIL-H5606 or MIL-H-83282. Air or nitrogen is to be filtered to remove 98 percent of all foreign matter whose two smallest &ensions are great& than 10 microns and to provide a dryness equivalent to dew point of -5g°F. 3-2. PROCEDURE. a. With shock strut compressed and in a vertical position, remove air-oil filler valve and fill with hydraulic fluid, Specification MIL-H-5606 or MILH-83282, to the level of filler port. Stroke the strut several times and recheck fluid level. Do not fill

through drain plug (4). Replace filler valve and inflate shock strut with dry air or nitrogen to 300 (110) psi allowing strut to extend. b. Maintain shock strut vertically for one hour. During this time, there should be no leakage of fluid past the glands. Then place shock strut in a horizontal position. Shock strut should not leak fluid past the gland during a one-hour test period. NOTE After vertical and horizontal test, shock strut assembly may be depressurized or left pressurized as best suited to maintenance needs. If shock strut assembly need be compressed without the weight of the airplane on it, air must be removed.

3-1/(3-2blank)

T.O. 452-233

SECTION IV NONDESTRUCTIVE INSPECTION INSTRUCTIONS 4-1. GENERAL. Nondestructive inspection of nose ar-l shock strut components is accomplished by ~ g n e t i ~ - ~ a r t imethod c l e (wet continuous) as set forth in Specification h!UL-1-6878 and T.O. 33B-1-1. Parts to be inspected are: a. NLG cylinder assembly (18, figure 2-11, made of 4340 steel heat treated to 260 to 280 ksi.

b. NLG piston assembly (251, made of 4340 steel heat treated to 260 to 280 h i . c. NLG fulcrum assembly (141, made of 4340 steel heat treated to 260 to 280 h i . EQUIPMENT AND MATERIALS. Equipment and materials needed to accomplish required magnetic inspections shall conform to requirements of Specifications MIL-1-6867 and MIL-1-6878 and shall include the following: a. Magnetic inspection unit, 6000 amps. b. Insulated central conductor, one to two inches in diameter. c. Standard field indicator, NSN 6635-00-3910058, or equivalent. d. Magnetic-particle concentrate and inspection oil conforming to Specification MIL-1-6868 and mixed as specified by T.O. 33B-1-1. 42.

Provide adequate ventilation during f luorescent-penetrant inspection. Wear protective gloves and prevent skin contact with solution and developer. 43. INSPECTION PROCEDURES. Perform magnetic-particle inspection in accordance with T.O. 33~-1-1applying the following factors: b. Set timing relay at 0.75 to 1.25 seconds. c. During magnetization and inspection process, comply with the following special instructions (see figures 4-1 and 4-2): (1) Allow magnetic-particle solution to drain a minimum of one minute after magnetizing. (2) Inspect inner and outer surfaces after each sequence of magnetizing shots.

(3) Position central conductor adjacent to part ID. (4) Maintain continuity of magnetic field direction at coil locations. (5) Position coil ID surface adjacent to part. d. Apply circular magnetization using an insulated central conductor and in accordance with table 4-1. e. Apply longitudinal magnetization in accordance with table 4-2. f. Demagnetize using standard demagnetizing procedure as specified in T.O. 33B-1-1. Residual magnetism in a part shall not cause a needle def lection of more than k2 points on a standard field indicator. 4-4. REJECTION CRITERIA. Reject part for any crack Inform 00-ALC/LPWE of any - questionable crack indications. 4-5. Items inspected per Specification MIL-1-6868 will use the following acceptancelrejection criteria: a. Nonmetallic inclusions may consist of entrapped oxides, silicates, sulfides, and other nonmetallic materials which appear as indications in magnetic-particle inspection. b. Laps, cracks, cold shuts, major surface, and embedded scale are not acceptable. c. Magnetic indications in high stress areas (fillets, edges, corners, keyways, holes, etc.) are unacceptable if they cannot be removed by blending. d. Magnetic indications on other surfaces are acceptable if they meet the following criteria: (1) Indicators are not visible when fluorescent inspected per Specification MIL-1-6866, Type I, Method B. (2) Magnetic indications in machined surfaces shall not exceed 318 inch in length for subsurface indications and 3/16 inch in length for surface indications. (3) Not more than 10 magnetic indications of any length per 40 square inches and not more than four magnetic indications of any length per one square inch will be permitted.

I

T.O. 482-23-3

\ FULCRUM ASSEMBLY 1

**'

INSULATED CONDUCTOR ROD

Figure 4-1. F'ulcrum and Cylinder Assemblies Magnetic Inspection Coil Locations and Conductor Positions

T.O. 4S2-23-3

INSUUTEI)

CONDUCTOR

ROD

Figure 4-2. Piston Assembly Magnetic Inspection Coil Locations and Conductor Positions

G8400158

1.0.452-23-3

Tabk 4-1. Circular Magnetization

FIGURE 2-1 INDEX NO.

PART NAME

CONDUCTOR POSITION NO.

CURRENT AND NUMBER OF SHOTS

25

Cylinder Assembly

1(figure 4-11

1000 amps, 90' apart, central conductor

32

Piston Assembly

1(figure 4-2)

1000 amps, 2 shots, 180' apart

2 (figure 4-2)

1000 amps, 4 shots, 90' apart

1(figure 4-11

1500 amps, contact shot

14

Fulcrum Assembly

T a b k 4-2. Longitudinal Magnetization

F'IGURE 2-1 INDEX NO.

PART NAME

CONDUCTOR POSITION NO.

CURRENT AND NUMBER OF SHOTS

25

Cylinder Assembly

A1 - A2 (figure 4-1)

1500 amps with 5-turn coil (7500 amp turns)

32

Piston Assembly

A1 - A2 (figure 4-2)

1500 amps with 5-turn coil (7500 amp turns)

B1- B2 (figure 4-2)

1500 amps with 5-turncoil (7500 amp turns)

A1 - A3 (figure 4-1)

1000 amps with 5-turn coil (5000 amp turns)

14

Fulcrum Assembly

T.O. 4S2-23-3

SECTION V NOSE LANDING GEAR BUILDUP INSTRUCTIONS 5-1. GENERAL. This section covers buildup instructions for the nose landing gear assembly, part No. 396175-13, using strut assembly, part No. 363590-1A. Additional nose landing gear assemblies are covered by difference data sheets in section VI. No special tools and test equipment are required for buildup other than a suitable support, sling or airplane nose landing gear attachments.

5-2. BUILDUP INSTRUCTIONS. Assemble the nose landing gear components onto the strut assembly in the order of the index numbers assigned to Figure 5-1.

a. Build up the nose landing gear assembly in accordance with the following instructions (see Figure 5-1): (1) Using grease, Specification M1L-G81322, lubricate the bearing surfaces, the splines, and the threads of the fulcrum (Figure 5-1, part of 1).

(2) Install spacer (2) onto the left-hand arm of the fulcrum (looking forward). (3) Install bearings (3), two places. (4) Install nuts (4), two places. (5) Cover the ends of the fulcrum with polyethylene or other suitable protective covering. (6) Install the strut assembly (1)in a holding fixture or the airplane to support the strut in the vertical position. (7) If not previously accomplished, service the strut in accordance with the applicable technical manual. (8) Install retainer (5), two places, in collar assembly (part of strut assembly (1)). (9) Install bearing (6) in each of the retainers (5). (10) Install bearing (6), two places, in bracket assembly (9). NOTE

lowered. This will prevent the keys slipping in the keyways. (11) Support the steering collar (7).

(12) Remove retainer screw and using a spanner wrench, loosen nut (8). (13) Lower nut (8) and bracket assembly (9). NOTE

Do not attach steering cylinder (11) rod ends to steering collar (7) a t this time. (14) Install two spacers (10) on each of the steering cylinders (11). A small piece of tape may be used to hold the lower spacers in position until the cylinders are installed. (15) Locate the steering cylinders (11)in the collar assembly and raise the bracket assembly (9) and nut (8). Screw on the nut sufficiently to locate the steering cylinders. (16) If tape was used to hold the spacers (10) in position, this must now be removed. (17) Using the spanner wrench, tighten the nut (8). Torque the nut to 210 (f10) foot-pounds. If necessary, back off on the nut only enough to align the lockscrew hole with the slot in the strut. (18) Install the lockscrew in nut (8), safetywire using lockwire, part No. MS20995C32. (19) Install shield (13) and ring (14) on each of the steering cylinder lower trunnions. (20) Install nut (16) on link end (17). (21)

Screw link end (17) into link end (18).

(22) Using bolt (19), washer (20), and nut (21), attach link end (18) to bracket assembly (22). (23) Install the bracket assembly (22) and Secure in place with pin (23), washers (24), and cotter pin (25). (24)

Install spacer (261, two places.

Ensure that the steering collar (7) is adequately supported before nut (8) is

Change 7

51

T.O. 4S2-23-3

(37) Remove pulley (42) and bolt (41) temporarily installed in subparagraph (31).

1

Prior to installing the manifold (27 and 331, ensure the steering cylinder (11) roll pin is aligned with the detent inside the manifold. Failure to line up the steering cylinder roll pin could cause damage to the nose landing gear system. (25) Build up manifold assembly (27) in accordance with paragraph 5-3. Install manifold assembly (27) in the left-hand position (looking forward), secure in position with two bolts (28), two washers (29), and two nuts (30). Tighten the nuts. (26) Install tube assemblies (31 and 32) in the manifold assembly (27). (27) Build up manifold assembly (33) in accordance with paragraph 5-3. Install the free ends of the tube assemblies (31 and 32) in the manifold assembly (33). (28) Install the manifold assembly (33); secure in position with two bolts (34), two washers (351, and two nuts (36). Tighten the nuts. (29) Loosely install link end (17) (of steering linkage) to steering valve (37); use bolt (38) to hold the link end (17) in place. (30) Install nut (39) with retainer (40) in the outboard position of bracket assembly (22). (31) Using bolt (41), temporarily install pulley (42) on the outboard end of bracket assembly (22). (32) With valve (37) in the neutral position, adjust the length of the steering linkage, as necessary, so that the center of the pulley of steering collar (7) is aligned with the bottom of pulley (42). The dimension between the top of the steering collar (7) and the bottom of the pulley (42) is to be 0.170 (fO.O1O) inch. (33) Tighten the nut (16) on the link end (17) and verify that the length of the steering linkage is unchanged; readjust length if necessary. (34) Verify that the bracket (22) will move the required travel without interference. (35) Safetywire the link end (17), nut (161, and link end (18) together using lockwire, part No. MS20995C32. Relative motion must be prevented in both directions. (36) Install washer (43) and nut (44) on bolt (38) holding steering linkage in place. Tighten nut finger tight and install cotter pin (45).

5-2 Change 7

(38) Install a nut (49), ring (481, and gasket (46) on end of two unions (47); lubricate with petrolatum, Federal Specification W-P-236. (39) Install one of the unions (47) in each of the steering cylinders (11). (40) Install a nut (53), ring (521, and gasket (50) on each of two unions (51); lubricate with petrolatum, Federal Specification W-P-236. (41) Install one of the unions (51) in each of the steering cylinders (11). (42) Lubricate the threads of unions (47 and 51) installed in subparagraphs (39) and (411, with petrolatum, Federal Specification W-P-236. (43) Lubricate the threads of elbows (56) and adjacent unions (Figure 5-2, 23 and 34), with petrolatum, Federal Specification W-P-236. (44) Install tube assembly (Figure 5-1, 541, two places. Tighten nuts (55) on elbows (56). Tighten fittings on tube assemblies. (45) Install tube assembly (57), two places; the longer arm of the tube assembly attaches to the upper union. Tighten the fittings. (46) Position the two elbows (58 and 59) on top of manifold assembly (27). The outboard elbow (58) should face 45 degrees aft and the inboard elbow (59) should face to the left. Tighten the two nuts (60). (47) Install arm assembly (61) with the grease fitting pointing downwards. Secure in position with bolt (62), washer (631, and nut (64). Tighten the nut only sufficiently to remove bolt endplay; tighten further only if required to align the cotter pin holes. Install cotter pin (65). The arm assembly should not fall under its own weight but still should move fairly easily. (48) Attach the rod ends for each steering cylinder (11)to the steering collar (7). Two seals (66) are installed per rod end. Secure each rod end with bolt (67), washer (681, and nut (69). Tighten the nuts finger tight and install cotter pins (70). (49) Install two nuts (74) and retainers (75) in the fulcrum of strut assembly (1). Attach bracket (71) to fulcrum using screw (72) in the forward position and screw (73) in the aft position.

T.O. 482-23-3

(50) Build up cylinder and tubing assembly (76) in accordance with paragraph 5-3. Install cylinder and tubing assembly (76) with the rod end grease fitting downwards; hold in position with bolt (77), washer (781, washer (79), washer (80) and nut (81). Tighten the nut. (51) Attach brace assemblies (82 and 83) to the strut assembly (1). Install bushings (84) and nuts (85). Tighten the nuts. (52) Install spacer (86) on the cylinder and tubing assembly (76) with the chamfer of the spacer facing the shoulder on the cylinder cap.

(53) Attach brace assemblies (82 and 83); secure in position with rings (87). (54)

Install bushing (89) and arm (90) on bolt

(91). (55) Install torque arm (92) with grease fitting forward. (56) bolt (91).

Hold torque arm (92) in position with

(57) Attach arm (93), washer (94), and nut (95); do not tighten a t this time.

Change 7 5-2.l/(5-2.2 Blank)

T.O. 4S2-233

1. 2. 3. 4. 5. 6.

7. 8.

9. 10. 11. 12. 13. 14. 15.

363590-1A SlRUT ASSEMBLY 338948 SPACER DP3SB BEARING (2 REQD) MS21025-28 NUT (2 REQD) 355844-1 RETAINER (2 REQD) KWB1555G BEARING (4 REQD) STEERING C O W (PARTOF 1) NUT (PARTOF 1) BRACKEiASSEMBLY (PART OF 1 ) 358019-1 SPACER (4 REQD) B95568-1 STEERING CWNDER (2 REQD) NOT USED 35617 5 1 SHIELD (2 REQD) MSl6624-1050 RING (2 REQD) 363725-1 PIN @RAG BRACE)

14

El TYPICAL BOTH STEERING CYLINDERS

Figure 5-1. Nose Landing Gear Assembly (Sheet 1 of 9)

T.O. 452-233

AN316-4R NUT 354553-1 LlNK END 345571 L l N K END NAS334CPA13 BOLT AN960-416 WASHER NAS679A4 NUT 339270 BRACKET ASSEMBLY AN394-49 PIN AN960-416L WASHER (2 REQD) MS24665- 15 1 COTTER PIN 351505 SPACER (2 REQD)

27. 28. 29. 30. 31 32. 33. 34

MANIFOLD ASSEMBLY AN174-15 BOLT (2 REQD) AN9600416 WASHER (2 REQD) MS21042-4 NUT (2 REQD) 354643- 1 TUBE ASSEMBLY 354643-8 TUBE ASSEMBLY M A N I F 0 LD ASSEMBLY A N 174- 15 BOLT (2 REQD) 35. AN96OD416 WASHER (2 REQD) 36. MS21042-4 NUT (2 REQD)

.

Figure 5-1. Nose Landing Gear Assembly (Sheet 2 of 9)

T.O. 4S2-233

7 (REF)

37. 38. 39. 40. 41. 42. 43. 44. 45. 46. 47. 48. 49. 50.

0-160 0*1m

0

6950694 VALVE ASSEMBLY (PART OF 27) AN173-6BOLT 2752-048 NUT LS48934 RETAINER AN4H14A BOLT MS20219-4 PULLEY AN960-10 WASHER AN310-3 NUT MS24665-134C O l T 3 PIN AN6290-6 GASKET (2 REQD) AN=-6 UNION (2 REQD) AN6291-6 RING (2 REQD) AN62846 NUT (2 REQD) AN62904 GASKET (2 REQD)

51. 52. 59. 54. 55. 56. 57. 58.

59. 60.

AN8326 UNION (2 REQD) AN62916 RlNG (2 REQD) AN62846 NUT (2 REQD) 342628285 TUBE ASSEMBLY (2 REQD) AN62896 NUT (2 REQD, SAME AS 18,29, FIGURE 5-2) AN833-6 ELBOW (2 REQD, SAME AS 21,32, FIGURE 5-2) 342628266TUBE ASSEMBLY (2 REQD) AN8334 ELBOW ( W E AS 57, FIGURE 52) AN8334 ELBOW (SAME AS 50, FIGURE 52) AN62898 NUT (2 REQD, SAME AS 47,54, FIGURE5-2)

Figure 5-1. Nose Landing Gear Assembly (Sheet 3 of 9)

G9100753

T.O. 4S2-23-3

TYPICAL BOTH

64

61. 62. 63. 64. 65. 66. 67. 68. 69. 70. 7 I. 72. 73. 74. 75.

3551 17-1 ARM ASSEMBLY 356028-1 BOLT AN960-1416 WASHER AN32C-14 NUT MS24665-359 COTTER PIN 351516 SEAL (4 REQD) NASI 108-221) BOLT (2 REQD) AN960-816 WASHER (2 REQD) AN320-8 NUT (2 REQD) MS24665-134 COTTER P I N (2 R 339269 BRACKET NAS5 17-4-7 SCREW NAS517-4-14 SCREW 2752-048 NUT (2 REQD) LS4893-4 RETAINER (2 REOD)

Figure 5-1. Nose Landing Gear Assembly (Sheet 4 of 9)

T.O. 4S2-233

76

-

396175-23 CYLINDER A N D TUBING ASSEMBLY

n. 338949 BOLT

78. 79. 80. 81 82. 83.

.

84.

85. 86. 87.

338956 WASHER MS20002C 12 WASHER MS20002- 12 WASHER 52NTE7627- 126 NUT 345726 BRACE ASSEMBLY 345726 BRACE ASSEMBLY NAS75-20-007 BUSHING (2 REQD) AN364-1614C NUT (2 REQD) 345731 SPACER MS16624-1200 R I N G (2 REQD)

Figure 5-1. Nose Landing Gear Assembly (Sheet 5 of 9)

T.O. 482-23-3

88. 89. 90. 9192.

93. 94. 95. 96. 97. 98. 99.

100. 101. 102. 103. 104. 105. 106. 107. 108. 109. 110. 1 11

.

NOT USED L52326-1850.120 BUSHING 353470-3 ARM 356028-1 BOLT 355205- 1 TORQUE ARM 353470-4 ARM AN960-1416 WASHER AN320-14 NUT MS20008-91 BOLT MS20002C8 WASHER AN960-816 WASHER 57585-820 NUT MS24665-359 COTTER P I N H3004 VIBRATION INSULATOR (2 REQD) 343060 LINK AN7-25 BOLT AN310-7 NUT 344070 BOLT AN960-1016 WASHER (3 REQD) NAS43HT10-24 SPACER (2 REQD) AN960-816 WASHER AN320-8 NUT MS24665-298 COTTER PIN AN7-25 BOLT

112. 1 13. 114. 115. 116. 117. 118. 119. 120. 121. 122.

AN310-7 NUT MS24665-298 COTTER PIN (2 REQD) 357918-1 FITTING 357771- 1 CROSSBAR AN6-12 BOLT AN310-6 NUT MS24665-134 COTTER PIN NOT USED NAS1104-18D BOLT (4 REQD) N O T USED MS21042-4 NUT (4 REQD)

Figure 5-1. Nose Landing Gear Assembly (Sheet 6 of 9)

T.O. 4S2-23-3

TOP VlEW

344069 CAP 355327-1 HANDLE ASSEMBLY AN4-15 BOLT AN310-4 NUT 3553261 BOLT MS24665-134 COTTER PIN 339271 CABLE ASSEMBLY MS24665-132 COTTER PIN (2 REQD) NAS42HT-6-32 SPACER

AN520-IOR 18 SCREW AN960-10L WASHER NAS679A3 NUT 339288 BRACKET N O T USED MS27039-1-21 SCREW (2 REQD) NOT USED AN960DlO WASHER (2 REQD) MS21042-3 NUT (2 REQD) C

Figure 5-1. Nose Landing Gear Assembly (Sheet 7 of 9)

T.O. 4S2-23-3

14 1. 142. 143. 144. 145. 146. 147. 148. 149. 150. 15 1. 152. 153. 154. 155. 156. 157. 158. 159.

2752-048 NUT MS202 19-4 PULLEY 339272-3 GUARD PIN (2 REQD) AN960D416 WASHER AN960-416LWASHER NAS1304- 15H BOLT 339272-3 GUARD PIN (2 REQD) AN960D416 WASHER AN960-416L WASHER 2752-048 NUT (2 REQD) LS4893-4 RETAINER (2 REQD) MS20219-4 PULLEY (4 REQD) AN960D416 WASHER (2 REQD) 339272-3 GUARD PIN (6 REQD) AN960-416L WASHER (4 REQD) AN4HlJA BOLT (2 REQD) AN4-24 BOLT AN310-4 NUT MS24665-134 COTTER PIN

Figure 5-1. Nose Landing Gear Assembly (Sheet 8 of 9)

T.O. 4S2-23-3

160. 337119 COLLAR (2 REQD) 161. 339242-3 WHEEL AND TIRE ASSEMBLY (2 REQD) 162. MS21258C39 WASHER (2 REQD) 163. MS21025-39 NUT (2 REQD) 164. NAS623-3-8 SCREW (2 REQD) 165. AN960-IOWASHER (2 REQD) 166. MS21042-3 NUT (2 REQD) 167. AN815-6 U N I O N (PART OF 76) 168. AN833-6 ELBOW (2 REQD, PART OF 76)

Figure 5-1. Nose Innding GearAssembly (Sheet 9 of 9)

T.O. 4S2-233

NOTE

Perform subparagraphs (58) through (60) only if a new arm (90 andlor 93) is being installed. (58) Swing arm (90) into position. k o m the other side of the strut, ream hole to 0.5000 to 0.5020-inch diameter using hole in the strut to locate the reamer. (59) Repeat subparagraph (58) for arm (93). Deburr arms (90 and 93). Refinish using brush alodine per Specification MIL-C-5541. (60) Clean the metal chips from the strut. (61) Secure arms (90 and 93) in position using bolt (961, washer (97) against bolt head, washer (981, and nut (99). Tighten the nut (99). (62) Tighten nut (95) installed in subparagraph (57) only enough to provide a drag on the torque arm (92) so that it requires from 1 to 15 footpounds to move the torque arm (92). (63) Install the two vibration insulators (101) in the strut assembly (1). (64) Position the link (102) so that the lower bolt (103) can be installed. Install the bolt (103) and attach nut (104). (65) Align the large hole in the link (102) and the hole in the strut (1);install bolt (105),three washers (1061, two spacers (1071, washer (108), and nut (109). Tighten the nut (109) finger tight only and install cotter pin (110). (66) Install bolt (111) in the upper hole in the link (102); attach nut (112). Tighten nut (112) and install cotter pin (113). (67) Tighten nut (104) installed in subparagraph (64) and install cotter pin (113).

The bolt, part No. AN6-12 (1161, is a safety link for tow overload protection. Do not substitute. (68) Attach fitting (114) to crossbar (115); secure in place with bolt (116) and nut (117). Tighten nut (117) and install cotter pin (118). (69) Install crossbar (115) in arms (90 and 93). Secure in position with four bolts (120) and nuts (122). Tighten the nuts. (70) Attach cap (123) to handle assembly (124); install bolt (125) and nut (126). Do not tighten nut (126) at this time; the nut and bolt are '

5-12 Change l

only being used to hold the cap and handle assembly together. (71) Position the arm (61) and torque arm (92) together and install bolt (127). Using the cap (123) and handle assembly (1241, tighten bolt (127) until the bolt head contacts the arm bushing. (72) Remove the cap and handle assembly (124) and reposition it so that it is displaced 45 degrees counterclockwise from the arm (61). Verify that the handle assembly can be rotated clockwise to align with the ann assembly (61) and that the handle will snap into the arm lug. (73) Unsnap the handle assembly (124) from the arm lug and back off on the bolt one-half turn. Tighten the nut (126) installed in subparagraph (70) and install cotter pin (128). (74) Completely unscrew and remove bolt (127) and separate arm assemblies (61 and 92). Replace the bolt (127) in the arm assembly (61); tighten the bolt; and snap the handle assembly into the arm lug. NOTE

Subparagraph (75) may be accomplished during operational checkout if the nose landing gear is assembled on the airplane. (75) Perform a checkout of the hydraulic steering system as follows: (a) Connect a hydraulic test set to the steering valve. The pressure line is attached to the elbow (58) and the return line to elbow (59). (b) Actuate the steering valve to the full right or left position and apply low hydraulic pressure. Bleed the steering cylinders to remove all of the air. Then increase pressure to 3700 psi and hold for one minute. There shall be no damage or evidence of leakage. (c) Repeat subpargraph (b) with the steering valve in the opposite extreme position. (dl Disconnect the hydraulic test set. (76) Attach cable assembly (129). The swaged bead fits in the collar pulley (7) and is held in position with two cotter pins (130). The longer end of the cable goes around the pulley in a clockwise direction when viewed from the top. (77) Route the longer end of the cable clockwise around the collar pulley. Install spacer (1311, screw (1321, washer (1331, and nut (134). (78) Route the other end of the cable around the collar pulley. Locate bracket (135) and secure in

I

T.O. 4S2-233

position with two screws (137), washers (1391, and nuts (140). (79) Install nut (141) in the bracket assembly (22) (inboard position). (80) Loosely attach inboard pulley (1421, two guard pins (1431, washer (1441, washer (1451, and bolt (146). Route the cable under and around the pulley (142). Locate the guard pins (143) and tighten bolt (145). Safetywire the bolt head with lockwire, part No. MS20995C32. (81) Loosely attach outboard pulley (421, two guard pins (1471, washer (1481, washer (1491, and bolt (41). Route the cable under and around the pulley (42). Locate the guard pins (147) and tighten bolt (41). Safetywire the bolt head with lockwire, part No. MS20995C32. (82) Install two nuts (150) and two retainers (151) in bracket (71). (83) Loosely install pulley (152), washer (1531, two guard pins (1541, washer (1551, and bolt (156) in the inboard rear position on bracket (71). Route the cable from pulley (142) over and around the pulley. Locate the guard pins (154) and tighten bolt (156). Safetywire the bolt head with lockwire, part No. MS20995C32. (84) Loosely install pulley (1521, washer (1531, two guard pins (154), washer (1551, and bolt (156) in the outboard rear position on bracket (71). Route the cable from pulley (42) over and around the pulley. Locate the guard pins (154) and tighten bolt (156). Safetywire the bolt head with lockwire, part No. MS20995C32. (85) Loosely install two pulleys (1521, two guard pins (1541, two washers (1551, bolt (1571, and nut (158) in the forward end of the bracket (71). Route the cables under the pulleys. Locate the guard pins (154) and tighten the nut (158). Install cotter pin (159). (86) Coil and tie the loose ends of the cable (129). (87) Install thread protector, part No. 340714, or equivalent, on each of the axle threads. (88) Pack wheel bearing assemblies (part of wheel and tire assembly (161)) with grease, Specification MIL-G81322. (89) Lubricate the axles with grease, Specification MIL-G81322. (90) Install collar (160) on each of the axles. (91) Place inboard bearing in each of the wheels and assemble grease seal, washer, and retaining ring.

(92) Place the wheels on the axles. (93) Remove the thread protectors. (94) Install outer bearing assemblies and washers. (95) Lubricate two washers (162) and two nuts (163) with grease, Specification MIL-G-81322, and install on axles. Tighten each nut (163) to 100 foot-pounds while manually rotating wheel; back off to zero but with all parts still seated. Retighten to 50 foot-pounds while manually rotating. wheel. If not a t a locking position, tightento nearest position. Install screw (1641, washer (1651, and nut (166) in each nut (163). (96) Cap exposed union (167) and four elbows (58,59, and 168). (97) Lubricate all grease fittings with grease, Specification MIL-G-81322. 53. SLI BASSEMBLY BUILDUP. Two manifold asembtubing assembly are required to be built up per landing gear assembly. a. Manifold Assembly Buildup. Right and left manifold assemblies are built up in accordance with the following instructions (see figure 5-21: Two valve assemblies are required to be built up per landing gear assembly (subparagraphs (1)through (14)). (1) Install valve (2, figure 5-2) in valve body (1).

(2) Install spring (3) and retainer (4). (3) Install gasket (5) on plug (6); lubrtcate with petrolatum, Federal Specification W-P-236. (4) Install plug ( 6 ) in valve body (1) and tighten. (5) Install packing (7)on plug (8); lubricate with petrolatum, Federal Specification W-P-236. (6) Install plug (8) in valve body (1). The shoulder of the plug should be flush with the face of the valve body and the flat on the plug should face plug (6). NOTE

If a previously used plug (8) is being used, omit subparagraph (7). (7) Using a No. 40 drill, drill through location holes in valve body (1)and plug (8).

d

BUILD UP OF MANIFOU) ASSEMBLY ON 352606

Figure 5-2. Manifold Assemblies (Sheet 1 of 3)

T.O. 4S2-233

BUILI? UP OF MANIFOLD ASSEMBLY ON 352605

45

Figure 5-2. Manifold Assemblies (Sheet 2 of 3)

T.O. 4S2-233

351515 VALVE BODY ( 2 REQD) 356353-1 VALVE ( 2 REQD) 337452 SPRING ( 2 REQD) 351514 RETAINER ( 2 REQD) AN62904 GASKET ( 2 REQD) AN81MDL PLUG ( 2 REQD) MS28775-008 PACKING ( 2 REQD) 8. 351502 PLUG ( 2 REQD) 9. NAS561P3-16 PIN ( 2 REQD) 10. 351503 RlNG (2 REQD) ll.MS28775222 PACKING ( 6 REQD) 12. MS35803-222 RlNG ( l 2 REQD) 13. 352606 MANIFOU) ASSEMBLY 14. 351506 WASHER 15. 1516624-3175 RlNG 16. AN62903 GASKET ( 2 REQD) 17. AN8144 PLUG ( 2 REQD) 18. AN6289-6 NUT 19. AN6291-6 RlNG 1. 2. 3. 4. 5. 6. 7.

20. 21. 22. 23. 24. 25. 26. 27. 28. 29. 30. 31. 32. 33. 34. 35. 36. 37. 38.

AN62906 GASKET MS21908-6 ELBOW AN62906 GASKET MS21902-6 UNION MS28774-112 RlNG ( 4 REQD) MS28775U.2 PACKING ( 2 REQD) 352605 MANIFOLD ASSEMBLY 351506 WASHER MS16624-1175 RlNG AN6289-6 NUT AN6291-6 RlNG AN62906 GASKET MSZi908-6 ELBOW AN62904 GASKET MSZi902-6 UNION MS28775-113 PACKING (2 REQD) 695069-3 VALVE ASSEMBLY MS20005-34 BOLT (2 REQD) MS2OOO2CS WASHER ( 2 REQD)

39. 40. 41. 42. 43. 44. 45. 46. 47. 48. 49. 50. 51. 52. 53. 54. 55. 56. 57.

AN960-516 WASHER (2 REQD) 57585-524 NUT ( 2 REQD) MS20005-30 BOLT 3 4 5 5 7 0 WASHER AN960-516 WASHER 5 7 5 8 5 5 2 4 NUT M S 2 8 7 7 4 - l l 2 RlNG ( 2 REQD) M S 2 8 7 7 5 l l 2 PACKING ( 2 REQD) AN6289-6 NUT M S 9 0 5 8 0 6 RlNG MS28778-6 GASKET AN833-6 ELBOW AN62904 GASKET MS21902-6 UNION AN6280-6 VALVE AN6289-6 NUT MS905&06 RlNG MS28778-6 GASKET AN833-6 ELBOW

Figure 5-2. Manifold Assemblies (Sheet 3 of 3)

( 8 ) Install pin (9).

(9) Using lockwire, part No. MS20995C32, safetywire plugs (6 and 8) together. (10) Install ring (10) on valve body (1). (11) Lubricate three packings (11)with petrolatum, Federal Specification W-P-236.

(12) Install one of the packings (11)in the groove nearest to the shoulder of the valve body (1). On either side of the packing ( l l ) , install rings (12). Position the rings so that the slits in the rings are 180 degrees apart. (13) Install the second packing (11)in the center groove of the valve body (1). On either side of the packing (111, install rings (12); position the rings so that the slits in the rings are 180 degrees apart. (14) Install the third packing (11) in the outer groove of the valve body (1). On either side of the packing (111, install rings (12); position the rings so that the slits in the rings are 180 degrees apart. (15) Install a valve assembly (built up in subparagraphs (1)through (14)) in manifold assembly (13). (16) Install washer (14) and hold washers and valve assembly in place with ring (15). (17) Install two gaskets (16) on two plugs (17) and lubricate with petrolatum, Federal Specification W-P-236. (18) Install the two plugs (17) in the manifold assembly (13) and tighten.

(19) Using lockwire, part No. MS20995C32, safetywire the two plugs (17) together. (20) Install nut (18), ring (191, and gasket (20) on elbow (21); lubricate with petrolatum, Federal Specification W-P-236. The nut (18) should be positioned such that the gasket (20) fits into the groove in the elbow (21) and not on the screw threads. (21) Install the elbow (21) in the valve assembly which is in the manifold assembly (13); tighten the elbow (31) and nut (18) finger tight. (22) Install gasket (22) on union (23); lubricate with petrolatum, Federal Specification W-P236. (23) Install the union (23) in the valve assembly, which is in the manifold assembly (13), and tighten. the

(24) Install a ring (24) in each of the holes in assembly (13).

(25) Lubricate the two packings (25) with petrolatum, Federal Specification W-P-236. (26) Install the packings (25) against the rings (24) installed in subparagraph (24). (27) Install two rings (24) against the packi n g ~(25) installed in subparagraph (26). (28) If the manifold assembly is not to be installed immediately, protect the unit from dust contamination. (29) Install a valve assembly (built up in subparagraphs (1)through (14))in manifold assembly (26).

T.O. 4S2-233

(30) Install washer (27); hold washer and assembly in place with ring (28). (31) Install nut (29), ring (30), and gasket (31) on elbow (32). Lubricate with petrolatum, Federal Specification W-P-236. The nut (29) should be positioned such that the gasket (31) fits into the groove in the elbow (32) and not on the screw threads. (32) Install the elbow (32) in the valve assembly, which is in the manifold assembly (26); tighten the elbow (32) and nut (29) finger tight. (33) Install gasket (33) on union (34). Lubricate with petrolatum, Federal Specification W-P236. (34) Install the union (34) in the valve assembly, which is in the manifold assembly (261, and tighten. (35) Lubricate two packings (35) with petrolatum, Federal Specification W-P-236. Position the two packings (35) in place on valve assembly (36). (36) Mount the valve assembly (36) on the manifold assembly (26). Secure in position with two bolts (37), two washers (381, two washers (391, and two nuts (40). The two bolts (37) with two washers (38) are installed on the manifold side in the two holes adjacent to each other. In the third hole, on the valve side, install a bolt (41) with washer (42). Secure on the manifold side with washer (43) and nut (44). Torque aIl three nuts to 175 (225) inchpounds. (37) Install a ring (45)in each of the two side holes in the valve assembly (36). (38) Lubricate two packings (46) with petrolatum, Federal Specification W-P-236.

(44) Install the union (52) in the valve assembly (36) and tighten. (45) Install valve (53) on the union which was installed in subparagraph (44). The direction of the flow arrow must point towards the union. (46) Install nut (541, ring (551, and gasket (56) on elbow (57). The nut should be positioned such that the gasket (56) fits into the groove in the elbow (57) and not on the screw threads. Lubricate with petrolatum, Federal Specification W-P-236. (47) Install the elbow (57) in the valve (53); tighten the elbow and nut finger tight. (48) If the manifold assembly is not to be installed immediately, protect the unit from dust contamination. b. Cylinder and Tubing Assembly Buildup. The cylinder and tubing assembly, part No. 39617523, is built up in accordance with the following instructions (see figure 5-31: (1) Lubricate ball (2, figure 5-31 with grease, Specification MIL-G81322, and install in rod end of cylinder assembly (1).

(2) Install bracket (3) using two bolts (4) and two washers (5). Tighten the bolts and safetywire using lockwire, part No. MS20995C32. (3) Install clamp (6) on cylinder (1). The centerline of the clamp should be 7.25 (M.25) inches from the flange at the opposite end of the cylinder from the rod end. Tighten the clamp only sufficiently to hold the clamp in place. NOTE

Prior to installation, lubricate all union and elbow threads and all gaskets with Petrolatum, Federal Specification W-P-236.

(39) Install the packings (46) against the rings (45) installed in subparagraph (37).

(4) Install union (7) with gasket (8) in cylinder assembly and tighten.

(40) Install two rings (45) against the pack(46) installed in subparagraph (39). ing~

(5) Install nut (91, ring (101, and gasket (11) onto the union (7). The nut (9) should be positioned such that the gasket fits into the groove in the union and not on the screw threads.

(41) Install nut (471, ring (481, and gasket (49) on elbow (50). The nut should be positioned such that the gasket fits into the groove in the elbow and not on the screw threads. Lubricate with petrolatum, Federal Specification W-P-236. (42) Install the elbow (50) in the valve assembly (36); tighten the elbow (50) and nut (47) finger tight. (43) Install gasket (51) on union (52). Lubricate with petrolatum, Federal Specification W-P236.

(6) Install valve (12) on the union (7); tighten nut (9) against the valve (12).

(7) Install union (13) with gasket (14) into valve (12) and tighten. (8) Install elbow (15) with nut (16), ring (17), and gasket (18) into valve (12). The nut (16) should be positioned such that the gasket fits into the groove of the elbow and not on the screw threads.

T.O. 4S2-23-3

(9) Install union (19)with gasket (20)into cylinder assembly (1). Tighten the union. (10) Very loosely attach two elbows (21)with two nuts (22)to the bracket (3). (11) Install tube assembly (23). Do not tighten fittings. (12) Install tube assembly (24). Do not tighten fittings. (13) Tighten the two nuts (22)on the two elbows (21)in the bracket (3). The elbows should be parallel to the union (19). (14) Tighten the nut (16)on the elbow (15) installed in the valve (12).

(15) Install spacer (25) and two clamps (28). Install washer (26)and attach nut (27)on clamp (6) and tighten. (16) Tighten the clamp (6)on the cylinder assembly (1). (17) Tighten the fittings of the tube assembly (23). (18) Tighten the fittings of the tube assembly (24). (19) Cap union (19)and two elbows (21).

T.O. 4S2-23-3

2

1. 3400770-1 CWNDER ASSEMBLY 2. KSU16-16 BALL 3. 396122-1 BRACKET 4. NAS1304-3H BOLT (2 REQD) 5. AN960D416 WASHER (2 REQD) 6. 909295-2ASH CLAMP 7. AN8324 UNION 8. STPlWW6GASKET 9. AN6289-6NUT 10. MS9058-06 RING 11. STSPK300-06GASKET 12. AN8277-6VALVE 13. AN8156 UNION 14. STSPK300-06 GASKET 15. AN833-6ELBOW 16. AN62846 NUT 17. MS9058-06 RING 18. STSPK3oo.06 GASKET 19. AN815-6 UNION 20. STSPK300-06GASKET 21. AN8334 ELBOW (2 REQD) 22 AN924-6 NUT (2 REQD) n. W~SB-615 TVBEE ASSEMBLY 24. 342628-613 TUBE ASSEMBLY 25. LS5987-10-24 SPACER 26. AN-1 0L WASHER 27. MS21042-3 NUT 28. MS21919DG6 CLAMP (2 REQD)

Figure 5-3. Cylinder and Tubing Assembly

519/(520 blank)

T.O. 4S2-233

SECTION VI DIFFERENCE DATA SHEETS 6-1. Overhaul test and NDI procedures for strut assemblies included in this section are the same as procedures for part No. 363590-1A except for specific differences noted by the applicable Difference Data Sheet. Sections I through IV contain complete overhaul, test, and NDI information for part No. 363590-1A 6-2. Bushing installation procedures for the torque arm assemblies included in this section are the same as procedures of section I1 except for specific differences noted by the applicable Difference Data Sheet. 6-3. Buildup instructions for the nose landing gear assemblies included in this section are the same as the instructions for part No. 396175-13in section V except for the specific differences noted by the applicable Difference Data Sheet. INDEX OF MODELS a. Strut Assemblies:

Part No. Page 7926486-10,-30,and -50.................................. 6-3 364653-2A,363590-5,and -7...........................6-5

Part No. Page 7926487-10..................................................... 6-7 7926829-10................................................... 6-15 371671-1.........................................................6-19 388071-1,-3,-5,and -9.................................. 6-33 3303591-1........................................................ 6-35 3303591-3,3314203-3,and 3316500-13..................................................6-43 9235508-10....................................................6-59 b. Torque Arm Assemblies: Part No. c.

Page

Nose Landing Gear Assemblies:

Part No.

Page

3001011-3....................................................... 6-73 388067-7and 388067-9..................................6-83 3303595-1a d 3303595-5.............................. 6-93 3314205-3.................................................. 6-107

6-1/(6-2blank)

T.O. 462-233

DIFFERENCE DATA S H E D

NOSE LANDING GEAR STRUT ASSEMBLY

PART NO. 7926486-10,30, AND -50

THE INSTRUCTIONS CONTAINED IN PRECEDING SECTIONS OF THlS TECHNICAL MANUAL APPLY EXCEPT FOR THE DIFFERENCES LISTED IN THlS DATA SHEET

LEADING PARTICULARS. Same as for part No. 371671-1. SPECLAL TOOLS. Same as for part No. 371671-1. DISASSEMBLY. Same as for part No. 371671-1. CLEANING. Same as for part No. 371671-1.

INSPECTION. Same as for part No. 371671-1. REPAIR OR REPLACEMENT. Same as for part No. 371671-1. TEST PROCEDURE. 371671-1.

Same as for part No.

6-3/(6-4 blank)

T.O. 4S2-23-3

DIFFERENCE DATA SHEET

NOSE LANDING GEAR SrRUT ASSEMBLY

PART NO. 364653-2A, 363590-5, AND -7

THE INSTRUCTIONS CONTAINED IN PRECEDING SECTIONS OF THlS TECHNICAL MANUAL APPLY EXCEPT FOR THE DIFFERENCES LISTED IN THlS DATA SHEET

LEADING PARTICULARS. Same as for part No. 363590-1A. SPECIAL TOOLS. Same a s for part No. 363590-1A DISASSEMBLY. Same as for part No. 363590-1A CLEANING. Same a s for part No. 363590-111 INSPECTION. Same as for part No. 363590-1A REPAlR OR REPLACEMENT. Same as for part No. 363590-lA, except a s follows: Steering Bracket Arms: Corrosion and other defects on the ID of the 1.43701 1.4378-inch steering cylinder hole may be removed to an ID of 1.6618 inches. Fabricate bushing from 4130 or 4340 steel 180 to 200 ksi to bring hole back to o~iginaldimension. Cadmium plate per Specification MIL-C-8837, Type II. Maintain 0.0004 to 0.0008 inch press fit.

TEST PROCEDURE. Same as for part No. 363590-1A MODIFICATION PROCEDURE. To m o d e strut, part No. 363590-14 into part No. 364653-2A configuration: Replace steering bracket, part No. 355845-1, with steering bracket, part No. 352607. Install two bushings, part No. 351519, in the steering arms of the outer cylinder, part No. 357370-601. Install the bushings with the flanges on the down side of the arms. Reidentifg as part No. 364653-211 Reidentifg part No. 363590-5 as part No. 364653-2A a t overhaul. Reidentify part No. 363590-7 a s part No. 363590-1A a t overhaul.

Pages 6-7 through 6-13 are deleted in their entirety. Change 1 65/(6-6 blank)

I

T.O. 452-23-3

DIFFERENCE DATA SHEET

NOSE LANDING GEAR STRUT ASSEMBLY

PART NO. 364653-2A, 363590-5, AND -7

THE INSTRUCTIONS CONTAINED IN PRECEDING SECTIONS OF THlS TECHNICAL MANUAL APPLY EXCEPT FOR THE DIFFERENCES LISTED IN THlS DATA SHEET

LEADING PARTICULARS. Same as for part No. 363590-1A SPECIAL TOOLS. Same a s for part No. 363590-1A DISASSEMBLY. Same as for part No. 363590-1A CLEANING. Same a s for part No. 363590-1A INSPECTION. Same as for part No. 363590-1A

REPAIR OR REPLACEMENT. Same as for part No. 363590-14 except as follows: Steering Bracket Arms:

TEST PROCEDURE. Same as for part No. 363590-1A MODIFICATION PROCEDURE. To modify strut, part No. 363590-14 into part No. 364653-2A configuration: Replace steering bracket, part No. 355845-1, with steering bracket, part No. 352607. Install two bushings, part No. 351519, in the steering arms of the outer cylinder, part No. 357370-601. Install the bushings with the flanges on the down side of the arms. Reidentlfy a s part No. 364653-2A Reidentify part No. 363590-5 as part No. 364653-2A at overhaul. Reidentlfy part No. 363590-7 a s part No. 363590-1A a t overhaul.

Corrosion and other defects on the ID of the 1.43701 1.4378-inch steering cylinder hole m a y be removed to an ID of 1.6618 inches. Fabricate bushing from 4130 or 4340 steel 180 to 200 ksi to bring hole back to original dimension. Cadmium plate per Specification MIL-C-8837, Type 11. Maintain 0.0004 to 0.0008 inch press fit.

65/(6-6 blank)

T.O. 4S2-233

DIFFERENCE DATA SHEET

NOSE LANDING GEAR STRUT ASSEMBLY

PART NO. 7926487-10

THE INSTRUCTIONS CONTAINED IN PRECEDING SECTIONS OF THlS TECHNICAL MANUAL APPLY EXCEPT FOR THE DIFFERENCES I-ISTED IN THlS DATA SHEET

LEADING PARTICULARS. Same as for part No. 371671-1 except weight is 251 pounds. DISASSEMBLY. (See figure 6-1.) Same as for part No. 371671-1for index Nos. 1through 36. For index Nos. 37 and up, disassemble in ascending order of index numbers assigned to figure 6-1.

CLEANING. Same as for part No. 371671-1. INSPECTION. Same as for part No. 371671-1 except a s follows: a. Substitute index numbers from figure 6-1 for similar parts in figure 6-4 and use table 6-5 for allowable service dimensions.

b. Original diameters for holes in cylinder (82) that hold shafts (65 and 70) are 2.437212.4383 inches; for crossbolt holes that hold bolts (64 and 69), original diameters are 0.878010.8790 inch in both cylinder (80) and shafts (65 and 70); for flange bolt holes that hold bolts (541, original diameters are 0.50110.508 inch in both cylinder (80) and collar (55); for ID of hole of collar (55) that mates with cylinder (801, original diameter is 5.250315.2517 inches. c. Inspect all (new and used) cylinders (80) to ensure that bolts (64 and 69) have been identified with the letter P stamped on bolt head. If bolts do not have the letter P, they will be removed and processed per subparagraph j., Repair and Replacement. REPAIR AND REPLACEMENT. Same as for part No. 371671-1 except as follows: a. Index Nos. 1through 36, 42 through 51,75, and 76 of figure 6-1 are same as part No. 371671-1. b. Cylinder (80) is 300M steel, heat-treated to 280 to 300 ksi. Shafts (65 and 70) are 4340 steel,

heat-treated to 200 to 220 ksi. Collar (55) is 300M steel, heat-treated to 280 to 300 ksi.

Provide adequate ventilation during cadmium plating. Wear protective gloves and chemical goggledface shield to prevent skin and eye contact. Local bioenvironmental engineer will provide information regarding specific respiratory and personal protective equipment requirements. c. Vacuum cadmium plate exterior surfaces of cylinder (80) except those surfaces that mate with collar (55). There is no maximum thickness on exterior surfaces except 0.0003 inch thiclmess on threads.

Provide adequate ventilation during cadmium plating. Wear protective gloves and chemical goggledface shield to prevent skin and eye contact. Local bioenvironmental engineer will provide information regarding specific respiratory and personal protective equipment requirements. d. Vacuum cadmium plate the 4,75014.752-inch interior surface (figure 6-51 to a thickness of 0.0001510.0006 inch.

DIFFERENCE DATA S H E E

(a) 2.437-inch diameter, grind to 2.422 inches minimum. Provide adequate ventilation during cadmium plating. Wear protective gloves and chemical goggledface shield to re vent skin and eye contact. Local bidenvironmental engineer will provide information regarding specific respiratory and personal protective equipment requirements. e. If damage or corrosion on large ID of collar (55, figure 6-11 is too extensive to bring back to original dimensions (5.250315.2517 inches) with vacuum cadmium plate, bore and chrome plate with MIL-STD-1501, Class 3, to original dimensions. M a x h u m plating thickness is 0.0075 inch.

a WARNING

Provide adequate ventilation during cadmium plating. Wear protective gloves and chemical goggledface shield to prevent skin and eye contact. Local bioenvironmental engineer will provide information regarding specific respiratory and personal protective equipment requirements. f. Chrome plate surfaces of cylinder (80) that mate with collar (55) per MIL-STD-1501, Type 11, Class 3. Plate (Type I) lower surface of bolt flange 0.001/0.0025 inch thick. Plate (Type II) cylinder wall that mates with collar (55) to after plating diameter of 5.248415.2498 inches. Maximum plating thickness is 0.0075 inch. g.

Rework of shafts (65 and 70).

All shotpeening, grinding, and abrasive blasting operations must be performed in an adeauatelv ventilated booth. Local bioe&ro&ental engineer will provide information regarding specific respiratory and personal protective equipment requirements.

(1) Damagelcorrosion may be removed from particular areas by grinding per MIL-STD-866 to the following dimensions: 6-8

to 1.860 (b) 1.8748-inch diameter,- grind inches minimum. NOTE

Remove only material required to clean up. (2) Nital etch per MIL-STD-867. (3) Chrome plate ground areas to sizes noted per MIL-STD-1501, Q p e 11, Class 3: (a) 2.422-inch minimum diameter, plate to 2-43712.436-inchdiameter; 63 RMS finish. (b) 1.860-inch minimum diameter, plate to 1.874811.8739-inch diameter; 63 RMS finish. (4) Radius toward splined area on 1.8748inch diameter to be 0.12 (+0.03) inch. ( 5 ) Chrome plate may run out on side of 0.1910.22-inch diameter relief cut.

(6) Chrome plate may run out on 0.0610.09inch radius of 2.437-hch diameter.

Provide adequate ventilation during cadmium plating. Wear protective gloves and chemical goggledface shield to prevent skin and eye contact. Local bioenvironmental engineer will provide information regarding specific respiratory and personal protective equipment requirements.

(7) Cadmium plate threads and splines per Specification MPC-8837, Type I, 0.0003 inch thick; cadmium plate all other surfaces per Specification MIL-C-8837, Type I, Class 1. (8) Crossbolt holes worn to a maximum diameter of 0.882 inch will be chrome plated back to size per MIL-STD-865. Finish dimension is 0.8791 0.878 inch. (9) Holes which cannot be repaired per subparagraph (8) will be reamed oversized to 0.93801 0.9375-inch diameter through. Install bushing, part No. 8930253-03. Coat OD of bushing with sealant, Specification MIL-S-81733, and - press bushing into plate while sealant is still damp. Bushing ends will not extend past OD of shaft.

T.O. 4S2-23-3 DIFFERENCE DATA SHEET

G8802178

Figure 6-1. Nose Landing Gear Strut Assembly, Part No. 7926487-10, Exploded View (Sheet I of 2)

T.O. 4S2-233

DIFFERENCE DATA SHEIT

1. 2. 3. 4. 5. 6. 7.

VALVE O-RING STANDPIPE O-RING BOLT WASHER BOLT 8. WASHER 9. JACK PLUG 10. NUT l i . WASHER 12. RETAINER 13. BUSHING 14. SETSCREW 15. GLAND NUT 16. PISTON 17. COlTER PIN 18. FLATHEAD PIN 19. RETAINER 20. BEARING 21. RETAINER 22. PIN 23. CAM 24. CAM 25. KEY 26. WASHER 27. SEAL ASSEMBLY

28. 29. 30. 31. 32. 33. 34. 35. 36. 37. 38. 39. 40. 41. 42. 43. 44. 45. 46. 47. 48. 49. 50. 51. 52. 53. 54.

BEARING FELT STRIP SCRAPER BACKUP RlNG O-RING PACKING BACKUP RlNG BULKHEAD NUT ORIFICE SCREW LOWER PLATE UPPER PLATE NUT BOLT SCREW NUT BRACKET KEY FllTING COLLAR BUSHING FITTING TAG SLEEVE NUT WASHER BOLT

55. 56. 57. 58. 59. 60. 61. 62. 63. 64. 65. 66. 67. 68. 69. 70. 71. 72. 73. 74. 75. 76. 77. 78. 79. 80.

COLLAR NUT WASHER BOLT FIRING BUSHING NUT WASHER WASHER BOLT SHAFT NUT BRACKET WASHER BOLT SHAFT NUT WASHER BOLT SPACER PIN BUSHING FITTING NAMEPLATE NAMEPLATE CYLINDER

Figure 6-1. Nose Landing Gear Strut Assembly, Part No. 7926487-10,Exploded View (Sheet 2 of 2)

h. Repair of pulley mounting lug is not applicable. Lug is a removable eye bolt on assemblies, part No. 3303591-1. Repairs to fulcnrm are not applicable on assemblies, part No. 3303591-1. i. Rework of through holes in trunnion of outer cylinder, part No. 3303589-1: (1) Holes worn to a maximum diameter of 0.882 inch will be plated back to size using chrome or nickel brush plating per MIL-STD-865. Alternate method is electroless nickel plate per Specification MIL-C-26074. Finish size is 0.87910.878 inch inside diameter.

Eye protection must be worn while involved in reaming operations. Also adequate ventilation must be provided when using sealing compound. Avoid prolonged or repeated skin contact. (2) Holes which cannot be repaired per subparagraph (1) will be reamed oversize to 0.9381 0.937-inch diameter through. Install bushing, part No. 8930253-01. Coat OD of bushing with sealant,

Specification MIL-S-81733, and press bushing into plate while sealant is still damp. Bushing ends will be flush with ID and OD of trunnion bore. Wipe off excess sealant after installation.

Provide adequate ventilation during plating operations. Provisions of AFOSH Standards 161-1, 161-2, and 127-31 will be strictly adhered to regarding adequacy of respiratory protection, ventilation, and personal protective clothing and equipment. j. Rework of through bolts (64 and 69). All bolts not identified with letter P on head will have bolt grip plated to a diameter of 0.877510.8770 inch. Plating may be chrome plate per MIL-STD-1501, Type I or II,Class 3, electroless nickel per Specification MIL-(2-2607, Class 2, Grade C; maintain a 32 RMS surface finish. Plating may fade out 1116 inch from head and 1116 inch from thread relief radius. Impression stamp or VIBRO ETCH letter P, 114inch high letters, at approximate center of bolt head after plating.

T.O. 4S2-23-3

DIFFERENCE DATA SHEET

Eye protection must be worn while involved in reaming and drilling operations. Also adequate ventilation must be provided when using sealing compound. Avoid prolonged or repeated skin contact. k. Rework of hole for shafts (65 and 70). Holes worn beyond 2.439-inch diameter will be reamed to 2.500/2.499-inch diameter through. Locally manufacture a bushing per figure 6-9. Coat OD of bushing with sealant, Specification MILS-81733, and press bushing inta place while sealant is still damp. Bushing will be flush with outboard end of fulcrum (trunnion). Wipe off excessive sealant after bushing installation. Ream holes for shafts (65 and 70) in bushings to 2.4372l2.4383. Drill two each 718 inch holes through bushing. Holes to be centered in existing 0.87810.879-inch diameter holes in cylinder. Ream holes for bolts (64 and 69) through bushing to 0.87810.879.

Provide adequate ventilation when using dry film lubricant. Wear protective gloves and prevent skin contact. Do not ingest. m. Treat threaded and keyways with dry film lubricant 5305 applied over cadmium plated surfaces. Overspray permissible; air-dry to cure. No post bake required.

n. Cylinders (80) with corroded lower gland nut threads may have new threads ground and undersize gland nut (15) installed. New threads should be 5.090-16UNS-3A, major diameter equals 5.0122l5.0088. (1) Nital etch per MIL-STD-867.

(2) Bake for four hours at 375 (e5)OF within four hours after grinding. (3) Vacuum cadmium plate per Specification MIL.C-8837, Type LT, 0.0003 inch maximum thickness on threads. (4) Undersize gland nut (151, part No. 8852955, should be used with this repaired cylinder.

All abrasive blasting operations shall be performed in an adequately ventilated booth. Local bioenvironmental engineer will provide information regarding specific respiratory and personal protective equipment requirements. Provide adequate ventilation during cadmium plating. Wear protective gloves and chemical goggledface shield to prevent skin and eye contact. Local bioenvironmental engineer will provide information regarding specific respiratory and personal protective equipment requirements. 1. Threaded area at lower end of steering collar area. Shallow corrosion to a maximum depth of 0.006 inch over entire surface may be grit blasted per MIL-STD-1504. Cadmium plate threads per Specification MIL-C-8837, Type I, 0.0003 inch thick.

o. Cylinders (80) with corroded steering mounting plate nut threads may have new threads ground and undersize nut (43) installed. (1) The first undersize repair will have new thread 5.220-16UN-3A, major diameter equals 5.220/5.2106, pitch diameter equals 5.179415.1737, minor diameter equals 5.143315.1388. Undersize nut (43), part No. 8852949-01, should be used with this repaired cylinder. (2) The second undersize repair will have new thread 5.185116UN-3A, major diameter equals 5.185015.1756, pitch diameter equals 5.14W5.1387, minor diameter equals 5.1083/5.1038. Undersize nut (431, part No. 8852949-03, should be used with this repaired cylinder.

(3) After either repair, processing must be accomplished:

the following

(a) Nital etch per MIL-STD-867. (b) Bake for four hours at 375 (&25)OF within four hours after grinding. (c) Vacuum cadmium plate per Specification MIL-C-8837, Type 11, 0.0003 inch maximum thickness on threads.

T.O. 4S2-23-3

DIFFERENCE DATA SHEET

(4) Identify rework cylinder (80) by making an X after part number found on raised stamp pad - on fulcrumusing an electric vibro etch tool. NONDESTRUCTION INSPECTION. Same as for part No. 363590-1A except as follows: a. NLG cylinder assembly (24, figure 6-3) is made of 300M steel, heat treated to 280 to 300 h i . b. Inspect cylinder as follows: Table 6-1. Circulcrr Magnetization

FIGURE 6-3

INDEXNO.

PART NAME Cylinder Assembly

24

CONDUCTOR POSITlON NO.

CURRENT

1 (Central Conductor)

1000 AMPS

2 (Head Shot)

2000 AMPS

3 (Head Shot)

2000 AMPS

LUBRICATION. Same as for part No. 371671-1 except a s follows: a. Coat faying surfaces of shaft (65 and 70, figure 6-71, bolts (64 and 69), collar (551, bolts (58), bolts (731, spacer (741, and all O-rings with 0-Lube (Parker Seal Co, 10567 Jefferson Blvd, Culver City, CA 90231). b. On bearing (28) apply grease, Specification MIL-A-81322, a t assembly as follows: (1) Coat liberally OD of bearing below O-ring and fill lightening grooves. (2) Coat sparingly ID below O-ring in bearing. (3) Coat mating surfaces of threads. c. Coat all mating surfaces of pin (75) and bushing (76) with grease, Specification MIL-G 81322.

Table 6-2. Longitudinal Magnetization

FIGURE 6-3

PART

INDEX NO.

NAME

24

Cylinder Assembly

COIL LOCATION NO. A1-A2

(Figure 6-2)

B1-B2 (Figure 6-2)

CURRENT 1500 AMPS with Sturn coil (7500 AMP turns) 1500 AMPS with Bturn coil (7500 AMP turns)

Figure 6-2. Cylinder Assembly Inspection Coil Location and Conductor Position, Part No. 3303589-1

T.O. 4S2-233

DlFfERENCE DATA SHEm

REASSEMBLY. Same as for part No. 371671-1 except a s follows: a. Assemble in descending order of index numbers assigned to figure 6-1. b. When installing shafts (65 and 70), ensure that spline tooth is on topside centerline of cylinder (80) and spline groove is on bottomside centerline. (See detail A, figure 6-1.) c. Seal joints on the following list with a bead of inhibited polysulfide, part No. PR1422G (B2) (Product Research Chemical Corp, 2919 Empire Ave, Burbank, CA 91504). Overcoat with coating, Specification MIL-C-83019. (1) Seal gland nut (15) to cylinder (80) joint and unused setscrew holes.

(2) Seal shafts (65 and 70) to cylinder (801, both ends. (3) Before sealing crossbolts (64 and 69) to cylinder (BO), both sides, torque each bolt to 780 to 900 inch-pounds. (4) Seal four flange bolts (54) to cylinder (80) and collar (55). (5) Seal joint between cylinder (80) flange and collar (55) flange. TEST PROCEDURE. Same as for part No. 371671-1.

6-13/(6-14 blank)

T.O. 4S2-23-3

DIFFERENCE DATA SHEf3

NOSE LANDING GEAR STRUT ASSEMBLY

PART NO. 7926829-10

THE INSTRUCTIONS CONTAINED IN PRECEDING SECTIONS OF THlS TECHNICAL MANUAL APPLY EXCEPT FOR THE DIFFERENCES LISTED IN THlS DATA SHEET

LEADING PARTICULARS. Same as for part No. 363590-1A except as follows: Weight .............................................. 250.9 pounds Fluid Capacity (approximate)..............................3.1 US quarts SPECIAL TOOLS. NATIONAL STOCK NO. 5120-00-675-0845 5120-00-6750833

DISASSEMBLY. (See figure 6-3.) Same as for part No. 363590-1A except as follows: The following parts indexed in figure 6-3 have been added: Wedge (231, Key (22), and Seal Assembly (47).

CLEANING. Same as for part No. 363590-1A. INSPECTION AND REPAIR. Same as for part No. 363590-1A except that the allowable service dimensions for index numbers listed in table 6-3 replace the corresponding numbers in table 2-2. LUBRICATION. (See figure 6-31. Before reassembly, immerse all internal gaskets, O-rings, backup, and bearing (49) in hydraulic fluid, Specification MIL-H-5606. Coat mating surfaces of gland nut threads with grease, Specification MIL-L-4343.

REASSEMBLY. (See figure 6-3.) Reassemble the shock strut assembly in the reverse order of disassembly noting the following exceptions and instructions: a. Replace all packings and backup rings as shown in figure 2-6. b. Before reassembly, immerse all internal packings, gaskets, and wiper rings in hydraulic fluid, Specification MIL-H-5606. c.

Lubricate exterior mating surfaces with

grease, Specification MIL-C-11796, and lubricate

pressure points with grease, Specification MIL-G 81322. d. Align the fulcrum and outer cylinder so that the fulcrum is perpendicular to the actuator attach lugs within 0.12 inch. Use the double adjustable key installation to obtain the alignment required. e. Torque screw (21, figure 6-3) from 150 to 175 inch-pounds in a counterclockwise direction. f. Torque the gland nut (33) from 90 to 110 foot-pounds; then back off to the nearest setscrew position and safetywire. PROCED&E. Same as for part No. 363590-1A

TEST

T.O.4S2-23-3

DIFFERENCE DATA SHEET

I .i.! I 'I!

Figure 6-3. Nose Landing Gear Strut Assembly, Part No. 7926829-10 (Sheet 1 of 2)

1. LOCKWIRE 2. VALVE 3. STAND PIPE 4. O-RING PACKING 5. DRAIN PLUG 6. GASKET 7. BUSHING 8. PIN 9. BUSHING 10. NUT l l . WASHER 12. WASHER 13. WASHER 14. BOLT 15. STRUT ASSEMBLY 16. FULCRUM ASSEMBLY 17. PLUG 18. NAMEPLATE 19. STRAP 20. DRIVE SCREW 21. SCREW 22. KEY 23. WEDGE 24. CYLINDER ASSEMBLY 25. FITTING 26. CORER PIN 27. NUT 28. WASHER

29. 30. 31. 32. 33. 34. 35. 36. 37. 38. 39. 40. 41. 42. 43. 44. 45. 46. 47. 48. 49. 50. 51. 52. 53. 54. 55. 56.

BOLT EXTENSION SHAFT LOCKWIRE SCREW GLAND NUT (LOOSEN) PISTON ASSEMBLY ADAPTER SPACER NUT COlTER PIN PIN RETAINER BEARING RETAINER PIN CAM CAM KEY SEAL ASSEMBLY BACKUP RlNG BEARING SCRAPER FELT BUSHING SCREW PLUG NUT WASHER

57. RETAINER 58. BULKHEAD 59. O-RING PACKING 60. BACKUP RlNG 61. NUT 62. ORIFICE ASSEMBLY 63. NUT 64. BOLT 65. WASHER 66. LOCKWIRE 67. SCREW 68. NUT 69. BRACKET ASSEMBLY 70. KEY 71. FITTING 72. COLLAR ASSEMBLY 73. FIRING 74. BUSHING 75. SLEEVE 76. TAG 77. NAMEPLATE 78. BUSHING 79. NAMEPLATE 80. COlTER PIN 81. NUT 82. WASHER 83. BOLT 84. MOUNT

Figure 6-3. Nose Landing Gear Strut Assembly, Part No. 7926829-10(Sheet 2 of 2)

T.O. 4S2-233

DIFFERENCE DATA SHEET Tabk 6-3. Replacement and Reconditioning Dimensions

(SEE FIGURE 6-3) INDEX NO.

PART NAME LOCALITY OF DIMENSION

8

Drag Pin

9

Bushing

69

Outer Cylinder DragPinHole Bracket (holes)

69

Bracket (key-

24

way)

78

Bushing

ORIGINAL DIMENSION

ORIGINAL CLEARROUNDNESS, ANCE CONCENTRICITY BETWEEN PARAUELISM PARTS

Center OD 1.37401 1.3748 Ends OD 1.24901 1.2498 OD 1.74981 1.7489 ID 1.37501 1.3760 1.75001 1.7519 1.3750 ID 1.3745 0.502 0.500

0.003 TIR 0.003 TIR

1.0019 ID 1.0000

0.003 TIR

ALLOWABLE SERVICE DIMENSIONS Center 1.3720 Min Ends 1.2470 Min

0.003TIR

Max 0.002

0.003TIR

Min 0.0002 1.3780ID Max

1.7470OD Min

1.7530Max 1.3760 ID

Max

0.5025 0.0025 Min (-)0.001 interference Max 1.0030ID 0.0037 Min 0.0008

DIFFERENCE DATA SHEET -

PART NO. 3 7 1 6 7 1 - 1

NOSE LANDING GEAR STRUT ASSEMBLY

THE INSTRUCTIONS CONTAINED IN PRECEDING SECTIONS OF THlS TECHNICAL MANUAL APPLY EXCEPT FOR THE DIFFERENCES LISTED IN THlS DATA SHEET

LEADING PARTICULARS. Same as for part No. 363590-18, except as follows:

...............................

Compressed Length. ..........................42.22 inches Weight ........................................170.9 pounds Hydraulic Fluid Capacity

NOMENCLATURE

b. Inspect upper bearing (19, figure 6-4) and lower bearing (27) for wear. Upper bearing outside diameter shall not measure less than 4.432 inches. Lower bearing inside diameter shall not measure more than 4.0042 inches. REPAIR OR REPLACEMENT. Same as part No. 363590-lA, except as follows:

SPECIAL TOOLS. PART NO.

a. Substitute index numbers from figure 6-4 for similar parts in figure 2-1 and use table 6-5 for allowable service dimensions.

NATIONAL STOCK NO.

WR-280

Gland Nut Wrench

5120-00-6750845

WR-341

Orifice Retaining Nut Wrench

5120-00-6750833

DISASSEMBLY. (See figure 6-4.) Same as for part No. 363590-lA, except as follows: a. Disassemble nose landing gear strut in index number sequence assigned to exploded view with exception that bushings (12 and 45, figure 6-41 will not be removed during overhaul unless determined unserviceable by dimensions indicated in table 6-5.

NOTE

All worn and corroded bolt holes shall be repaired in accordance with figure 6-5. a. Wear or damage exceeding table 6-5 and figure 6-5 shall be reworked. b. All machining operations shall be accomplished using flood coolant techniques. Coolants, tooling, and operating techniques shall be consistent with state-of-the-art as relates to cutting, boring, reaming, honing, and milling steel products (4340) heat treated to 200 to 280 ksi level.

CLEANING. Same as for part No. 363590-1A

c. Shotpeen: Use No. 230 steel shot at 0.010 inch to 0.014 inch A2 intensity per Specification MIL-S-13165.

INSPECTION. Same as for part No. 363590-lA, except as follows:

d. 6-4.

Vacuum cadmium plate areas noted in table

T.O. 4S2-233

DIFFERENCE DATA SHEET

' I \

\4

Figure 6-4. Nose Landing Gear Strut Assembly, Part No. 371671-1, Exploded View (Sheet 1 of 2)

T.O. 4S2-233 DIFFERENCE DATA SHEET

1. AIR VALVE ASSEMBLY 2. STAND PIPE 3. O-RING PACKING 4. BOLT 5. WASHER 6. BOLT 7. WASHER 8. JACK PLUG 9. NUT 10. WASHER 11. RETAINER 12. BUSHING 13. SCREW 14. GLAND NUT 15. PISTON ASSEMBLY 16. COllER PIN 17. FLATHEAD PIN 18. RETAINER 19. BEARING 20. RETAINER 21. PIN 22. CAM 23. CAM 24. KEY

25. 26. 27. 28. 29. 30. 31. 32. 33. 34. 35. 36. 37. 38. 39. 40. 41. 42. 43. 44. 45. 46. 47. 48.

WASHER SEAL ASSEMBLY BEARING FELT SCRAPER BACKUP RlNG O-RING PACKING BACKUP RlNG BULKHEAD NUT ORIFICE NUT WASHER BOLT SCREW NUT BRACKET ASSEMBLY KEY FITTING COLLAR BUSHING FITTING TAG SLEEVE

49. 50. 51. 52. 53.

54. 55. 56.

57. 58. 59. 60. 61. 62. 63. 64. 65. 66. 67. 68. 69. 70.

71.

NUT WASHER BOLT WASHER WASHER FITTING BUSHING NUT WASHER BOLT WASHER WASHER BOLT WASHER SIDE STRUT ASSEMBLY PIN BUSHING SCREW KEY WEDGE FULCRUM ASSEMBLY NAMEPLATE CYLINDER ASSEMBLY

Figure 6-4. Nose Landing Gear Strut Assembly, Part No. 371671-1, Exploded View (Sheet 2 of 2) Table 6-4. Vacuum Cadmium Plate Amas

PART DESCRIPTION (SEE FIGURE 6-41 Side Strut Assembly (63) Steering collar (44) part No. 352604 Steering Cylinder Bracket Assembly (41) part No. 355845

AREAS TO PLATE Entire outer surface and end hole ID. AU over, except where chrome plated. All over, except ID if it is chrome plated.

T.O. 492-23-3

DIFFERENCE DATA SHEET

e. Outer cylinders (71, figure 6-41, part Nos. 371675-1 and 371675-7, corroded to extent that corrosion cannot be removed within service wear limits specified in table 6-5, shall be reworked in accordance with the following criteria:

0.050 inch from outboard intersection of internal chamfer. Finish grind to 4.75014.752 inches in diameter.

NOTE

(c) Third Repair. Lower bearing bores from which corrosion cannot be removed at 4.767 inches will be ground to 4.79814.802 inches diameter.

Vacuum cadmium plate all external surfaces not chrome plated, including lugs, lug ID, steering flanges, and bearing areas (figure 2-2). (1) LOWER BEARING AREA

(a) First Repair. Remove isolated corrosion by local polishing providing isolated corrosion does not extend into seal area. Local rework will be limited to one and one-half bands of corrosion not over one inch in height. A minimum wall thickness of 0.080 inch shall remain after rework. (b) Second Repair. Remove more extensive corrosion from lower bearing area by boring, honing or grinding the bore oversize to 4.767 inches maximum in accordance with Specification MILSTD-866.

-1 Bake. 2 Shotpeen. 3 Mask inside diameter of cylinder, inside diamiter of fillet radius, threads and other surfaces that would be affected by plating runout or fume concentrations. 4 Chrome plate to original dimension. -5 Bake.

6 Grind and chamfer to drawing specification. Rbout plating from maximum to minimum on inside of bearing bore between 0.020 and

-7 Bake.

(dl An additional localized pit removal over 20 percent of area will be permitted except in seal area one inch down from inner chamfer. Pit removal is to be accomplished by hand polishing. Maintain a minimum wall thickness of 0.080 inch. Shotpeen prior to plating. (el Mask bearing bore as in subparagraph (b)3. Chrome plate and grind to 4.78514.787 inches. h p l i n g in chrome plate over localized rework area after final finish is permissible.

Maintain minimum plating thickness of 0.0005 inch. NOTE

If lower bearing bore was ground over-

size, 4.785/4.787, install oversize bearing, part No. 67C30138. Ensure that dimension of bearing is 4.780314.7825. Apply 0.000310.0005 inch cadmium plate to standard and oversize bearings. Prior to installation, fill lightening grooves in bearings with grease, Specification MIL-G-81322.

Table 6-5. Allowable Service Dimensions REPAIR DIMENSIONS PART NO.

AND LOCATION (See figure 6-4) Outer cylinder drag pin hole

Bushing (65)

Bushing (65)

ORIGINAL DIAMETER MIN

MAX

MIN

MAX

MIN

MAX

0.0002

0.003

---

1.7530

0.006

---

PLATING REPAIR OR REPLACEMENT PART

MACH FINISH

MACH OVERSIZE

68D29135-43

63

0.006

68D29135-43

1.565

0.005

BUSHING INTERFERENCE MIN

MAX

1.8702

0.0002 Loose Fit

0.003 Loose Fit

100

---

---

---

68D29135-43

100

---

---

---

1.7500

1.7519

ID

1.7489 OD

1.7498 OD

0.0002

0.003

1.7470

0.0003

0.002

.--

0.0003

0.002

1.560

---

0.005

---

100

---

---

---

---

---

---

0.753

0.0045

68D29135-35

63

0.8704

0.0006

0.0015

---

---

---

---

---

68D29135-33

63

1.3073

0.0007

0.0019

---

.-.

...

..-

.--

68D29135-33

125

--.

---

---

1.066

0.006

68D29135-33

125

--.

---

---

1.5635

ID

Drag brace pin (64)

1.5615 OD

1.5623 OD

Drag brace attach lugs (71 and 69)

0.7500

0.7509

ID

ID

Actuator attach lugs (71)

1.1875

1.1885

Bushings (55)

1.1890 OD

1.1898 OD

Bracket (41)

REWORK LIMITS

ID

1.5625

Steering cylinder attach holes (71)

MAX

CLEARANCE

CLEARANCE

ID

Bushings (55)

SERVICE TOLERANCE

1.0625

m

1.0634

2.0000

2.0011

ID

ID

1.3745

ID

0.0002

0.0019

---

---

---

---

--.

..-

68D29135-39

63

2.199

0.001

0.0027

---

---

---

-.-

---

68D29135-49

63

1.5993

0.0007

0.0019

ID

1.3750

m

Table 6-5. Allowable Service Dimensions (Cont)

PART NO. AM)

LOCATION (See figure 6-4) TA attach lug (44)

ORIGINAL DIAMETER

CLEARANCE

MAX

MIN

MAX

MIN

1.3750

1.3760

---

---

---

ID

ID 0.0002

0.002

---

MIN

REWORK LIMITS

SERVICE TOLERANCE

REPAIR DIMENSIONS

MAX

--.

MAX CLEARANCE

PLATING REPAIR OR REPLACEMENT PART

BUSHING INTERFERENCE

MACH FINISH

MACH OVERSIZE

MIN

MAX

---

68D29135-53

63

1.4993

0.0007

0.0014

0.005

68D29135-53

125

---

---

---

---

68D29135-53

125

---

---

---

1.125

1.126

ID

ID

Bushing (45)

1.3765 OD

1.3773 OD

---

---

.-.

Steer cylinder attach lugs (44)

0.5000

0.5010

---

---

---

0.503

---

68D29135-51

63

0.06243

0.0007

0.0014

Side brace (63)

0.7500

0.7509

---

---

--.

0.753

0.0045

68D29135-47

63

0.8694

0.0006

0.0013

TA attach lug (15)

1.3750 ID

1.3760 ID

---

---

---

--.

---

68D29135-27

63

1.4993

0.0007

0.002

Bushing (12)

1.3765 OD

1.3760 OD

---

---

-..

...

-..

68D29135-83

125

---

---

---

0.0002

0.002

0.006

69D29135-83

125

---

---

---

Bushing (45)

Bushing (12)

1.125

1.126

ID

ID

---

1.128

--.

1.129

T.O. 4S2-233

DIFFERENCE DATA SHEET

NOTE ON ONE-PIECE OUTER CYLINDERS, PART NO. 3 3 0 3 B 1 , THE FOLLOWING DIMENSIONSAPPLY ON ACTUATOR FACE-TO-FACE BASE METAL 1 2 10 (+ 0.010) INCHES BUSHING FLANGE-0.050 INCH, AND FACE-TO-FACE WITH BUSHINGS 1.110 (+ 0.010) INCHES.

THD-I-14NF-3A

1.1898 1.1890

Figure 6-5. Replacement and Reconditioning Dimensions (Sheet 1 of 2)

OD

T.O. 452-23-3

DIFFERENCE DATA SHEET

'

ACCEPTABLE TO REMOVE UPTO 0.020 lNcn MATERIAL1 SIDE EITHER LOCALLY OR ENTIRE AREA FROM DIMENSIONS SHOWN ON ORIGINAL BLUE PRINT SHOT PEEN REWORKED AREA. (BELOW STEP SEAL TO PISTON BOTTOMI

THREADS 2 7 / 1 6 - 1 6 ~ - 3 ~

Figure 6-5. Replacement and Reconditioning Dimensions (Sheet 2 of 2)

E I ~ E RREMOVE LOC*LLY OR ENTIRE AREA. SHOT P E W REWORKEDAREAS.

T.O. 482-233

DIFFERENCE DATA SHEET

(2) PULLEY MOUNTING LUG UPPER. (a) A bent lug may be straightened by applying sufficient force to the lug to restore it to its proper pasition. Shotpeen the affected areas 0.0101 0.014 inch A2 intensity per Specification MIL-S13165. Bake four hours at 375 (k25)"F' and magnetic-particle inspect per T.O. 33B-1-1 for crack indications. If cracks appear, repair in accordance with subparagraph (b).

11

WARNING

11

Provide adequate ventilation during f luorescent-penetrant inspection. Wear protective gloves and prevent skin contact with solution and developer. (b) Broken and cracked lugs shall be repaired by boring the broken lugs (left or right) on the centerline of the attached lug as shown in figure 2-5. Counterbore the bottom 0.100 inch deep as shown in figure 2-5. Ream and hone, as noted, to establish the final ID 0.897/0.898 of the hole as shown. Shotpeen the hole ID surfaces 0.01010.014 inch AZ intensity per Specification MIL-S-13165. Magnetic-particle inspect for cracks per T.O. 33B-1-1. Apply wet sealer, Specification MIL-S81733, to ID and press bushings, part No. 68D29135-91,into place. Machine the top portion of the bushing to conform to the contour shown in figure 2-5. Drill and ream the 0.250010.2508 inch hole as shown. (3) FULCRUM ATTACHING SURFACE. (a) Remove defects from the fulcrum attaching surface by locally polishing not to exceed 30 percent of the surface area nor more than 0.030 inch in depth. (b) If defects exceed 30 percent of the surface area, grind to remove defects but not less than 4.474-inch outside diameter. Corrosion pits remaining after grinding to 4.474 inches may be removed by locally polishing to remove defects. Limit local rework to 30 percent of area and to 0.030 inch maximum depth. NOTE

On initial grind, increase the radius surfaces to match the new tangents.

-1 Bake. -2 Shotpeen.

3 Chrome plate. Mask all keyways and radius~urfacesto prevent plating runout in these areas.

4.4986.

-4 Bake. -5 Grind to finish dimensions, 4.4998/ -6 Bake.

(4) Remove corrosion from exterior surfaces of the outer cylinder as follows: (See figure 6-6.) (a) Remove paint and superficial corrosion Der a ~ ~ l i c a bdirectives. le (b) Remove corrosion pits by locally polishing the cylinder between A-A and B-By figure 6-6. The area of rework shall not reduce the cylinder wall thickness less than 0.015 inch below minimum drawing specification. (c) Locally polish defects between B-B and C-C, figure 6-6 (except steering collar mating surfaces), down to 0.010 below the minimum wall thickness. If all defects are not removed, they may be polished out to a depth of 0.030 inch below minimum wall thickness provided they do not exceed 30 percent of the circumference. (dl Locally polish defects between C-C and D-D, figure 6-6 not to exceed 0.015 inch below minimum wall thickness. (el Remove defects fiom the webs of the steering arms by locally polishing not to exceed 0.030 inch maximum depth. (f) Rework the drag pin hole in the top of the cylinder by boring and honing the hole to remove corrosion pits but not to exceed 1.8702-inch inside diameter. Machine bushing, part No. 68D29135-43, to provide an 0.0002/0.003 loose fit and install with drag- -pin,. part No. 371674-1. -

( 5 ) Remove corrosion and other defects h m the lower centering cam keyway by hand polishing. Do not widen or deepen the keyway by more than 0.005 inch. Blend all polishing into surrounding areas with fillet radii of a t least 0.030 inch. Shotpeen the keyway in accordance with instructions outlined in this manual.

f. PistonIAxle 355400-1.

Assembly

(151,

Part

No.

(1) Vacuum cadmium plate all external surfaces not chrome plated, including lugs, lug IDS, and bearing areas. Plate ID of axle. Plating on ID of piston is optional (figure 2-3).

T.O. 4S2-233

DIFFERENCE DATA SHEET

Figure 6-6. Outer Cylinder Corrosion Removal

T.O. 4S2-233

DIFFERENCE DATA SHEtT

(2) Locally polish minor blemishes in the chromium plate within 3.993-inch diameter. (3) If plated surface is worn beyond tolerance or damaged, recondition as follows: (a) Strip chromium plate. (b) Grind to a 3.980-inch maximum, remove defects, and polish the 0.500 inch radius below the chromium plate to a 32 RMS or better finish. Maintain a minimum wall of 0.155 inch. (c) Bake.

(dl Shotpeen. (el Chromium plate.

(fl Bake.

Nital etch inspection must be accomplished by qualified personnel only. -4 Nital etch inspect. -5 Bake.

-6 Shotpeen. -7 Chrome plate. -8 Bake. 9 Grind inner journals to 2.99981 2.9990-inch-diameter and outer journals to 2.49901 2.4998-inch diameter. 10 Bake. -

(g) Grind to 3.995313.9975-inch dimeter; diameter to be concentric with 0.002 TIR. (4) Inspect the wheel bearing journals of the axle for wear, scoring, galls, and pits. (a) On the outer bearing journals, minor blemishes may be locally polished provided: 1 No more than 20 percent of the bearing area is affected by the polishing.

2 Depth of the polishing does not exceed 0.038 inch. r journals, minor (b) On the i ~ e bearing blemishes may be locally polished provided: 1 Not more than 10 percent of the bearing area is affected by polishing to a depth not to exceed 0.010 inch.

radius.

2 No pit edge is sharper than 0.060 -

3 No more than 30 percent of any one square inch-of area is affected by polishing. (c)

If damage is more extensive:

1 Grind the inner journals sufficiently

to remove &fats not to exceed 0.015 inch material removal on the diameter maintaining 0.120 inch maximum wall thickness.

2 Grind the outer journals to remove defects not-to exceed 0.020 inch minimum outer diameter. 3 Bake. -

Provide adequate ventilation during fluorescent-penetrant inspection. Wear protective gloves and prevent skin contact with solution and developer. 11 Magnetic-particle inspect per Specification m-I-6868C. g. Fulcrum Assembly (69, figure 6-41, Part Nos. 371672-1, 388072-1, and 388072-9. NOTE

Vacuum cadmium plate all surfaces not chrome plated including lugs, lugs ID, and bearing areas, except do not plate internal cavities of fulcrum assembly (figure 2-41. (1) Locally polish the cylinder attaching surfaces inside diameter to remove corrosion pits not to exceed 20 percent of the surface area or 0.015 inch deep. If more extensive rework is required, grind the fulcrum inside diameter to 4.516 inches maximum. Locally polish remaining pits not to exceed 20 percent of the surface area 0.007 inch deep. Chrome plate and grind to original drawing dimensions. NOTE

1116 inch may be masked off to provide machine reference. (2) Grind pitted, galled or scored fulcrum bearing journals sufficiently to remove defects not

T.O. 4S2-23-3

DIFFERENCE DATA SHEET

less than 2.4210 inches (minimum) diameter. Remaining isolated pits shall be removed by locally polishing to a depth of 0.010 inch and not to exceed 20 percent of the affected area.

(c) Magnetic-particle inspect internal cavities of fulcrum; use a borescope to facilitate inspection. The presence of cracks shall be cause for rejection.

(3) Bake after grinding operations.

Nital etch inspection must be accomplished by qualified personnel only. (4) Nital etch inspect. (5) Bake. (6) Shotpeen. (7) Mask areas adjacent to the journals to ensure plating does not run out on the radius and relief. (8) Chrome plate. (9) Bake. (10) Grind fulcrum ID to 4.50014.501 and trunnion OD to 2.43712.436 inches. (11) Bake. (12) If actuator attach lugs are cracked or corroded, remove lugs sufficiently to remove crack or corrosion indications by machining or milling. Surface finish shall be 63 RMS or better. Cutting operations shall be under flood cooling conditions. Nital etch inspect following cutting operations in accordance with MIL-STD-867, as applicable. Shotpeen rework area to 0.010/0.014 inch A2 intensity in accordance with Specification MIL-S-13165B. (13) Inspect internal cavities of fulcrum. If weld spatter in the area of pressure weld approximately 13inches from end of fulcrum has previously been removed and treated per subparagraphs (a) through (i) and sealant coating is intact, no further action is required. If spatter exists on either side of the weld, proceed as follows:

If spatter has previously been removed and sealant is not intact comply with subparagraphs (e) through (i). (a) Remove majority of weld spatter using a wire brush or emery cloth butterflymounted in an air or electric drill. (b) Remove any remaining spatter or corrosion by shotpeening the area using the right angle shotpeen nozzle.

Provide adequate ventilation when using l,l,l-trichloroethane. Wear protective gloves and prevent skin contact. To prevent formation of hazardous products, do not expose to high temperatures, flame or spark. (dl Clean interior of fulcrum with l , l , 1-trichloroethane, Federal Specification 0-T-620. (el Plug small hole in keyway of fulcrum assembly and fill the cavity with acetone, Federal Specification 0-A-51C; hold for 15 minutes and drain. Dry at 90 to 14g°C (200 to 300T1.

(fl Completely fill cavities with sprayable sealant per Specification MZLC-38713A or MIL-S-81733 and drain. NOTE Curing time with low pressure forced air, for polysulfide sealant at room temperature, is eight hours. (g) Remove plugs installed in subparagraph (e) and cure for four hours with low pressure forced air at 49 to 60°C (120 to 140°F) with fulcrum in a horizontal position.

(h) Reinstall plugs; refill cavities with a second coat of polysulfide sealant; drain cavities; and remove plugs. (i) Allow sealant to dry for 24 hours.

1 Impression stamp DS on the two 1-112 inch expansion plugs with 3/16 inch letters and install one in each end of fulcrum. h. Steering collar sleeve (48, figure 6-41, part No. 340876. (1) If not previously accomplished, rework keyway slot depth to 0.625 inch maximum to obtain an 0.090/0.110 inch radius in comers.

(2) If cracks are evident in keyway corner and do not exceed 1/32 inch in depth, smooth and blend in with radius.

T.O. 4S2-23-3

DIFFERENCE DATA SHED

(3) Vacuum cadmium plate ID and end per MIL-STD-870, Type II. i. Steering collar (441, part No. 352604. (1) Remove corrosion from inside diameter by locally polishing or grinding sufficiently to remove defects but not to exceed 0.030 inch in depth or 35 percent of surface area. Maintain a finish of 32 RMS surface roughness with a minimum radius of 0.050 inch blending reworked area into parent metal. (a) Shotpeen reworked surface. Fade shotpeening on surfaces adjacent to reworked areas.

(b) Bake as per subparagraph 2-4.b.(3). (2) If corrosion cannot be removed in accordance with subparagraph (11, grind ID oversize 0.030 inch. (a) Isolated pits remaining after grind shall be removed by locally polishing to a depth of 0.020 inch. (b) Shotpeen ID. (c) Bake as per subparagraph 2-4.b.(3). (dl Chrome plate ID per MIL-STD-1501, Type 11, Class 3. (el Grind ID to 5.500015.5014 inches. (fl Bake as per subparagraph 2-4.b.(3). (3) If corrosion still remains after grinding at 5.530 inches, grind ID to maximum of 5.540 inches for flame spray repair. Flame spray per MIL-STD-869 using METC0451 material. Finish grinding ID to final dimension of 5.500015.5014 inches. (4) Remove corrosion from plane surfaces of steering collar (area adjacent to 5.5000-inch bore) by locally polishing but not to exceed 0.020 inch depth. Do not exceed more than 20 percent of either surface. Grind either or both surfaces 0.020 inch maximum per MIL-STD-866. Chrome plate either or both surfaces, as required, and finish grinding to final dimension of 2.74812.750 inches. j. Gland nut (14). Drill two 0.1250 (+0.00151 -0.0000) inch diameter holes, 180 degrees apart and 0.387 inch above bottom face of gland nut (14). Install lubrication fitting, part No. NAS-516-1, in each hole. k. Steering bracket (41), part No. 355845-1.

(1) Grind inside diameter of steering bracket to remove corrosion but not to exceed 5.272

inches. Locally polish isolated pits as required up to 0.040 inch depth maximum not to exceed 30 percent of circumference. Remove corrosion on flat surfaces by locally polishing or air blasting with aluminum oxide grit or suitable substitute until corrosion products are removed. Corrosion removal shall be limited to 45 percent of surface area and 0.030 inch maximum depth. (2) Chrome plate ID and grind to 5.2501 5.252 inches in accordance with MILSTD-1501, Type 11, Class 2, and MIGSTD-866. (3) Corrosion and other defects on ID of 1.374511.3750-inch steering cylinder hole may be removed to an ID of 1.5993 inches. The 1.170-inch diameter opening at bottom of this hole should not be enlarged. Walls of reworked portion of hole should be blended with bottom of hole using a 0.0101 0.030 inch fillet radius. Chamfer of OD of the 68D29135-49 bushing shall be increased to 45 degrees by 0.03010.035 inch. LUBRICATION. Before reassembly, coat entire interior of strut cylinder and exterior of piston with hydraulic fluid, Specification MIL-H-5606. In addition, presoak all packings in hydraulic fluid, Specification MIL-H-5606, before installation andlor assembly. Lubricate pressure lubrication points with grease, Specification MIL-G81322. REASSEMBLY. (See figure 6-4.) Reassemble shock strut assembly in reverse order of disassembly. NOTE

AU bolts and fittings are to be torqued in accordance with T.O. 1-1A-8 unless otherwise specified. During reassembly of fulcrum and outer cylinder, replace key, part No. 370456-1, with adjustable key (671, part No. 370455-2, and wedge (681, part No. 370454-2. Align Wcrum and outer cylinder so that fulcrum is perpendicular to actuator attach lugs within 0.02 inch. Ensure that fit between fulcrum and outer cylinder is 0.0002 minimum clearance (sliding fit, not interference fit). a. During reassembly, seal mating surface edges between fulcrum (69) and outer cylinder (71) with sealing compound, Specification MIL-S-8802, Class B-Y2. Seal thread joint, locking grooves, and unused lock screw holes of gland nut (14).

T.O. 4S2-233

DIFFERENCE DATA SHEET

b. Special Torque Values. Lower gland nut, part No. 373517-1, is to be torqued to 90 to 110 footpounds and backed off to nearest setscrew position (14).

c. Assemble fulcrum to outer cylinder and ensure that actuator attach lugs are perpendicular to fulcrum to within k0.002 inch.

TEST PROCEDURE. 363590-1A

Same as for part No.

T.O. 4 S 2 - 2 3 3

DIFFERENCE DATA SHEET

NOSE LANDING GEAR STRUT ASSEMBLY

PART NO. 388071-1, -3, -5, AND -9

THE INSTRUCTIONS CONTAINED IN PRECEDING SECTIONS OF THlS TECHNICAL MANUAL APPLY EXCEPT FOR THE DIFFERENCES LISTED IN THlS DATA SHEET

LEADING PARTICULARS. Same as for part No. 371671-1. SPECIAL TOOLS. Same a s for part No. 371671-1. DISASSEMBLY. Same a s for part No. 371671-1. CLEANING. Same a s for part No. 371671-1. INSPECTION. Same a s for part No. 371671-1. REPAIR OR REPLACEMENT. Same as for part No. 371671-1, except as follows: Part Nos. 388071-5 and 388071-9: Use plug button, part No. SS48172 (Carr Fastener Corp, Cambridge, MA), to plug the

open 0.63010.635-inch diameter hole located on the right side of the axle below the piston. Install with sealant, Specification MIL-S-8802, Class B2. TEST PROCEDURE. 371671-1.

Same a s for part No.

Reidentify part No. 388071-1 a s part No. 388071-3 a t overhaul. Reidentify part No. 388071-5 a s part No. 371671-1 a t overhaul. Reidentify part No. 388071-9 a s part No. 388071-3 a t overhaul.

633/(6-34

blank)

T.O. 4S2-233

DIFFERENCE DATA SHEET

NOSE LANDING GEAR STRUT ASSEMBLY

PART NO. 3303591-1 and 7926847-10

THE INSTRUCTIONS CONTAINED IN PRECEDING SECTIONS OF THlS TECHNICAL MANUAL APPLY EXCEPT FOR THE DlFFERENCES LISTED IN THlS DATA SHEET

LEADING P A R T I C W S . Same as for part No.

\, :

371671-1 except weight is 251 pounds. DISASSEMBLY. (See figure 6-7.) Same as for part No. 371671-1 for index Nos. 1through 36. For index Nos. 37 and up, disassemble in ascending order of index numbers assigned to figure 6-7. CLEANING. Same as for part No. 371671-1. INSPEC!l'ION. Same as for part No. 371671-1 except as follows: a. Substitute index numbers from figure 6-7 for similar parts in figure 6-4 and use table 6-5 for allowable service dimensions. b. The original diameters for holes in cylinder (80, figure 6-71 that hold shafts (65 and 70) are 2.437212.4383 inches; for cross-bolt holes that hold bolts (64 and 691, original diameters are 0.87801 0.8790 inch in both cylinder (80) and shafts (65 and 70); for flange bolt holes that hold bolts (54), original diameters are 0.50110.508 inch in both the cylinder (80) and collar (55); for ID of the hole of collar (55) that mates with cylinder (80), original diameter is 5.250315.2517 inches. c. Inspect all (new and used) cylinders (80) to ensure that bolts (64 and 69) have been identified with the letter P stamped on bolt head. If bolts do not have the letter P, they will be removed and processed per subparagraph j., Repair and Replacement. REPAIR AND REPLACEMENT. Same as for part No. 371671-1 except as follows: a. Index Nos. 1through 36,42 through 51,75, and 76 of figure 6-7 are the same as part No. 371671-1. b. Cylinder (80) is 300M steel, heat treated to 280 to 300 ksi. Shafts (65 and 70) are 4340 steel,

heat treated to 200 to 220 ksi. Collar (55) is 300M steel, heat treated to 280 to 300 ksi.

Provide adequate ventilation during cadmium plating. Wear protective gloves and chemical gogglesffaceshield to prevent skin and eye contact. The local bioenvironmentai engineer will provide information regarding specific respiratory and personal protective eauipment reauirements. c. Vacuum cadmium plate the exterior surfaces of cylinder (80) except those surfaces that mate with collar (55). There is no maximum thickness on exterior surfaces except 0.0003 inch thickness on threads.

Provide adequate ventilation during cadmium plating. Wear protective gloves and chemical goggledface shield to prevent skin and eye contact. The local bioenvironmental engineer will provide information regarding specific respiratory and personal protective equipment requirements. d. Vacuum cadmium plate the 4.75014.752-inch interior surface (figure 6-51 to a thickness of 0.0001510.0006 inch.

Change 1 G35

T.O. 4S2-23-3

DlfTERENCE DATA SHEIT

1

Provide adequate ventilation during cadmium plating. Wear protective gloves and chemical goggledface shield to prevent skin and eye contact. The local bioenvironmental engineer will provide information regarding specific respiratory and personal protective equipment requirements. e. Collar Assembly (55, figure 6-11, part No. 3303583-11-5: (1) Grind ID to maximum of 5.2667 inches per MIL-STD-866 to remove corrosion and pitting. Chrome plate ID per MILSTD-1501, Type 11,Class 3. Finish grinding ID to final dimension of 5.25031 5.2517 inches. (2) If corrosion still remains after grinding ID at 5.2667 inches, grind ID to maximumof 5.2850 inches for flame spray repair per MILSTD-869 using METCO 451 material. Sulfamate nickel plating per MIL-STD-868 may be used as an alternate method. Finish grinding ID to final dimension of 5.250315.2517 inches. (3) If collar bolt (54) holes are corroded or worn to 0.510 inch, holes will be reamed oversize to 0.562510.5632 inch. Install bushing, part No. 9418192-01, using standard shrink-fit method. Apply wet sealant per Specification MIL-S-81733 to ID of holes prior to bushing installation. Final ream bushing ID to 0.50110.503 inch. (4) Remove corrosion from the entire plane surface area of collar assembly (areas adjacent to 5.2517-inch bore) by grinding either or both surfaces. The 2.750 inch face-to-face thickness will not be reduced below 2.720 inches during grinding. Chrome plate face-to-face thiclmess per MIL-STD1501, Type 11,Class 3, and finish grinding to 2.7401 2.760 inches. Sulfamate nickel plating per MILSTD-868 may be used as an alternate method.

Provide adequate ventilation during cadmium plating. Wear protective gloves and chemical goggledface shield to prevent skin and eye contact. The local bioenvironmental engineer will provide information regarding specific

636

Change 2

respiratory and personal protective equipment requirements. f. Chrome plate surfaces of cylinder (80) that mate with collar (55) per MILSTD-1501, Type II, Class 3. Plate (Type I) the lower surface of bolt flange 0.001/0.0025-inch thick. Plate (Type 11) the cylinder wall that mates with collar (55) to after plating diameter of 5.248415.2498 inches. Maximum plating thickness is 0.0075 inch. g. Rework of shafts (65 and 701, part Nos. 3303588-1-1-3 and 3332994-1.

AU shotpeening, grinding, and abrasive blasting operations must be performed in an adequately ventilated booth. The local bioenvironmental engineer will provide information regarding specific respiratory and personal protective equipment requirements. (1) Damage/corrosion may be removed f h m particular areas by grinding per MIL-STD-866 to the following dimensions: (a) 2.437-inch diameter; grind to 2.422 inches minimum. (b) 1.8748-inch diameter; grind to 1.860 inches minimum. NOTE

Remove only material required to clean up. (2) Nital etch per MIL-STD-867. (3) Chrome plate ground areas to sizes noted per MIL-STD-1501, Type 11, Class 3. (a) 2.422-inch minimum diameter; plate to 2.43712.436-inch diameter; 63 RMS finish. (b) 1.860-inch minimum diameter; plate to 1.874811.8739-inch diameter; 63 RMS finish. (4) Radius toward splined area on 1.8748inch diameter to be 0.12 (f0.03) inch. (5) Chrome plate may run out on side of 0.1910.22-inch diameter relief cut. (6) Chrome plate may run out on 0.0610.09inch radius of 2.437-inch diameter.

1

T.O. 452-23-3

DIFFERENCE DATA SHEET

Provide adequate ventilation during cadmium plating. Wear protective gloves and chemical goggleslface shield to prevent skin and eye contact. Local bioenvironmental engineer will provide information regarding specific respiratory and personal protective equipment requirements. (7) cadmium plate threads and splines per Specification MIL-C-8837, Type I, 0.0003-inch thick cadmium plate all other surfaces per Specification MIL-C-8837, Type I, Class 1.

I I

(8) Cross bolt holes worn to a maximum 0.882 inch will be plated back to size of 0.87910.878inch using chrome plating per MIL-STD-1501 or nickel brush plating per MILSTD-865.

(9) Holes which cannot be repaired per subparagraph (8) will be reamed oversized to 0.93751 0.9380 inch diameter through. Install bushing, part No. 8930253-03 on shaft, part No. 3303588-1/-3 and bushing, part No. 8930253-05 on shaft, part No. 332994-1, using the standard shrink-fit method. Apply wet sealant per Specification MILS-81733 to ID of holes prior to bushing installation. Bushing ends will not extend past OD of shaft.

(2) Holes which cannot be repaired per subparagraph (1)will be reamed oversize to 0.9375/ 0.9380-inch diameter through. Install bushing, part No. 8930253-01, using the standard shrink-fit method. Apply wet sealant per Specification MILS-81733 to ID of trunnion bore prior to bushing installation. Bushing ends will be flush with ID of trunnion bore.

Provide adequate ventilation during plating operations. Provisions of AFOSH Standards 161-1, 161-2, and 127-31 will be strictly adhered to regarding adequacy of respiratory protection, ventilation, and personal protective clothing and equipment. j. Rework of through bolts (64 and 69). All bolts not identified with letter P on head will have bolt grip plated to a diameter of 0.877510.8770 inch. Plating may be chrome plate per MIL-STD-1501, Type I or 11, Class 3, electroless nickle per Specification MIL-C-2607, Class 2, Grade C; maintain a 32 RMS surface finish. Plating may fade out 1/16 inch from head and 1/16 inch from thread relief radius. Impression stamp or VIBRO ETCH letter P, 114inch high letters, a t approximate center of bolt head after plating.

h. Repair of pulley mounting lug is not applicable. Lug is a removable eye bolt on assemblies, part No. 3303591-1. Repairs to fulcrum are not applicable on assemblies, part No. 3303591-1. i. Rework of through holes in trunnion of outer cylinder, part No. 3303589-1:

(1) Holes worn to a maximum of 0.882 inch (inside diameter) will be plated back to size of 0.8791 0.878 inch using chrome plating per MIL-STD-1501 or nickel brush plating per MIL-STD-865. Alternate method is electroless nickel plate per Specification MILC-26074.

I

Eye protection must be worn while involved in reaming operations. Also adequate ventilation must be provided when using sealing compound. Avoid prolonged or repeated skin contact.

Eye protection must be worn while involved in reaming and drilling operations. Also adequate ventilation must be provided when using sealing compound. Avoid prolonged or repeated skin contact. k. Rework of hole for shafts (65 and 70). Holes worn beyond 2.439-inch diameter will be reamed to 2.50012.499-inch diameter through. Install bushing, part No. 9418192-03. Coat OD of bushing with sealant, Specification MIL-S-81733, and press bushing into place while sealant is still damp. Bushing will be flush with outboard end of fulcrum (trunnion). Wipe off excessive sealant after bushing installation. Ream holes for shafts (65 and 70) in bushings to 2.4372l2.4383. Drill two each 718inch holes through bushing. Holes to be centered in

I

T.O. 4S2-23-3

DIFFERENCE DATA SHEET

existing 0.87810.879-inch diameter holes in cylinder. Ream holes for bolts (64 and 69) through bushing to 0.87810.879.

(3) Vacuum cadmium plate per Specification MIL-C-8837, Type 11, 0.0003-inch maximum thickness on threads. (4) Undersize gland nut (15), part No. 8852955, should be used with this repaired cylinder. Stencil on the nut, using black polyurethane paint, UNDERSIZED GLAND NUT - INSTALLED.

All abrasive blasting operations shall be performed in an adequately ventilated booth. Local bioenvironmental engineer will provide information regarding specific respiratory and personal protective equipment requirements. Provide adequate ventilation during cadmium plating. Wear protective gloves and chemical goggledface shield to prevent skin and eye contact. Local bioenvironmental engineer will provide information regarding specific respiratory and personal protective equipment requirements. 1. Threaded area at lower end of steering collar area. Shallow corrosion to a maximum depth of 0.006 inch over entire surface may be grit blasted per MIESTD-1504. Cadmium plate threads per Specification MILC-8837, Type I, 0.0003-inch thick.

o. Cylinders (80) with corroded steering mounting plate nut threads may have new threads ground and undersize nut (43) installed. (1) The first undersize repair will have new thread 5.220-16UN-3A, major diameter equals 5.22015.2106, pitch diameter equals 5.1794/5.1737, minor diameter equals 5.143315.1388. Undersize nut (43), part No. 8852949-01, should be used with this repaired cylinder. (2) The second undersize repair will have new thread 5.185-16UN-3A, major diameter equals 5.185015.1756, pitch diameter equals 5.144445.1387, minor diameter equals 5.108315.1038. Thread relief groove above threads must be recut to 5.09015.095 diameter. Undersize nut (431, part No. 8852949-03, should be used with this repaired cylinder.

(3) After either repair, processing must be accomplished:

the

following

(a) Nital etch per MILSTD-867 (b) Bake for 4 hours a t 375 (k25)"F within 4 hours after grinding.

Provide adequate ventilation when using dry film lubricant. Wear protective gloves and prevent skin contact. Do not ingest. m. Treat threaded and keyways with dry film lubricant 5305 applied over cadmium plated surfaces. Overspray permissible; air-dry to cure. No post bake required. n. Cylinders (80) with corroded lower gland nut threads may have new threads ground and undersize gland nut (15) installed. New threads should be 5.090-16UNS-3A, major diameter equals 5.090015.0806, pitch diameter equals 5.0494l5.0437, minor diameter equals 5.013315.0088. (1) Nital etch per MIL-STD-867.

(2) Bake for 4 hours at 375 (-5)OF within 4 hours after grinding.

6-38 Change 5

(c) Vacuum cadmium plate per Specification MIGC-8837, Type 11, 0.0003-inch maximum thickness on threads. (d) With two undersize repair nuts, the part number of the nut being used must be stenciled on the nut as follows, UNDERSIZED STEERING NUT 8852949-01 (OR -03) INSTALLED, using a black polyurethane paint for the stencil. (4) Identify reworked cylinder (80) by making an X after part number found on raised stamp pad on fulcrum, using an electric vibro etch tool. p. Cylinders (80) with flange bolts (54) holes, that are corroded or worn to 0.510 inch will be reamed oversized to 0.562510.5632 inch. Install bushing, part No. 9418192-01, using standard shrink-fit method. Apply wet sealant per Specification MIL-S-81733 to ID of holes prior to bushing installation. Final ream bushing ID to 0.50110.503 inch.

T.O. 4S2-23-3 DIFFERENCE DATA SHEET

Provide adequate ventilation during cadmium plating. Wear protective gloves and chemical goggledface shield to prevent skin and eye contact. Local bioenvironmental engineer will provide information regarding specific respiratory and personal protective equipment requirements. (7) Cadmium plate threads and splines per Specification MILC-8837, Type I, 0.0003-inch thick cadmium plate all other surfaces per Specification MIL-C-8837, Type I, Class 1. (8) Cross bolt holes worn to a maxjxnum 0.882 inch will be plated back to size of 0.87910.878inch using chrome plating per MILSTD-1501 or nickel brush plating per MIL-STD-865. (9) Holes which cannot be repaired per subparagraph (8) will be reamed oversized to 0.93751 0.9380 inch diameter through. Install bushing, part No. 8930253-03 on shaft, part No. 3303588-1/-3and bushing, part No. 8930253-05 on shaft, part No. 332994-1, using the standard shrink-fit method. Apply wet sealant per Specification MLS-81733 to ID of holes prior to bushing installation. Bushing ends will not extend past OD of shaft. h. Repair of pulley mounting lug is not applicable. Lug is a removable eye bolt on assemblies, part No. 3303591-1. Repairs to Mcrum are not applicable on assemblies, part No. 3303591-1. i. Rework of through holes in trunnion of outer cylinder, part No. 3303589-1: (1) Holes worn to a maximum of 0.882 inch (inside diameter) will be plated back to size of 0.8791 0.878 inch using chrome plating per MIL-STD-1501 or nickel brush plating per MIL-STD-865. Alternate method is electroless nickel plate per Specification MIL-C-26074.

I !

I

Eye protection must be worn while involved in reaming operations. Also adequate ventilation must be provided when using sealing compound. Avoid prolonged or repeated skin contact.

(2) Holes which cannot be repaired per subparagraph (1) will be reamed oversize to 0.93751 0.9380-inch diameter through. Install bushing, part No. 8930253-01; using the standard shrink-fit method. Apply wet sealant per Specification MILS-81733 to ID of trunnion bore prior to bushing installation. Bushing ends will be flush with ID of trunnion bore.

Provide adequate ventilation during plating operations. Provisions of AFOSH Standards 161-1, 161-2, and 127-31 will .be strictly adhered to regarding adequacy of respiratory protection, ventilation, and personal protective clothing and equipment. j. Rework of through bolts (64 and 69). All bolts not identified with letter P on head will have bolt grip plated to a diameter of 0.871510.8770 inch. Plating may be chrome plate per MILSTD-1501, Type I or II,Class 3, electroless nickle per Specification MIL-C-2607, Class 2, Grade C; maintain a 32 RMS surface finish. Plating may fade out 1/16 inch from head and 1/16 inch from thread relief radius. Impression stamp or VIBRO ETCH letter P, 1/4inch high letters, a t approximate center of bolt head after plating..

Eye protection must be worn while involved in reaming and drilling operations. Also adequate ventilation must be provided when using sealing compound. Avoid prolonged or repeated skin contact. k. Rework of hole for shafts (65 and 70). Holes worn beyond 2.439-inch diameter will be reamed to 2.50012.499-inch diameter through. Install bushing,part No. 9418192-03. Coat OD of bushing with sealant, Specification MIL-S-81733, and press bushing into place while sealant is still damp. Bushing will be flush with outboard end of fulcrum (trunnion). Wipe off excessive sealant after bushing installation. Ream holes for shafts (65 and 70) in bushings to 2.437212.4383. Drill two each 718inch holes through bushing. Holes to be centered in

Change 2 6-37

I

T.O. 482-233

DIFFERENCE DATA SHEET

existing 0.87810.879-inch diameter holes in cylinder. Ream holes for bolts (64 and 69) through bushing to 0.87810.879.

All abrasive blasting operations shall be performed in an adequately ventilated booth. Local bioenvironmental engineer will provide information regarding specific respiratory and personal protective equipment requirements. Provide adequate ventilation during cadmium plating. Wear protective gloves and chemical goggledface shield to prevent skin and eye contact. h c a l bioenvironmental engineer will provide information regarding specific respiratory and personal protective equipment requirements. 1. Threaded area at lower end of steering collar area. Shallow corrosion to a maximum depth of 0.006 inch over entire surface may be grit blasted per MIL-STD-1504. Cadmium plate threads per Specification MILC-8837, Type I, 0.0003-inch thick.

Provide adequate ventilation when using dry film lubricant. Wear protective gloves and prevent skin contact. Do not ingest. m. Treat threaded and keyways with dry film lubricant 5305 applied over cadmium plated surfaces. Overspray permissible; air-dry to cure. No post bake required. n. Cylinders (80) with corroded lower gland nut threads may have new threads ground and undersize gland nut (15) installed. New threads should be 5.090-16UNS-3A, major diameter equals 5.090015.0806, pitch diameter equals 5.04945.0437, minor diameter equals 5.013315.0088. (1) Nital etch per MIL-STD-867. (2) Bake for four hours at 375 (e5I0F within four hours after grinding.

6-38 Change 2

(3) Vacuum cadmium plate per Specification MIL-(2-8837, Type II, 0.0003-inch maximum thickness on threads. (4) Undersize gland nut (151, part No. 8852955, should be used with this repaired cylinder. Stencil on the nut, using black polyurethane paint, UNDERSIZED GLAND NUT INSTALLED. o. Cylinders (80) with corroded steering mounting plate nut threads may have new threads ground and undersize nut (43) installed. (1) The first undersize repair will have new thread 5.220-16UN-3A, major diameter equals 5.22015.2106, pitch diameter equals 5.179U5.1737, minor diameter equals 5.143315.1388. Undersize nut (431, part No. 8852949-01, should be used with this repaired cylinder. (2) The second undersize repair will have new thread 5.185-16UN-3A, major diameter equals 5.185015.1756, pitch diameter equals 5.1444l5.1387, minor diameter equals 5.108315.1038. Thread relief groove above threads must be recut to 5.09015.095 diameter. Undersize nut (431, part No. 8852949-03, should be used with this repaired cylinder. (3) After either repair, the following processing must be accomplished: (a) Nital etch per MTLSTD-867. (b) Bake for four hours at 375 (f25)OF within four hours after grinding. (c) Vacuum cadmium plate per Specification MIL-C-8837, Type 11, 0.0003-inch maximum thickness on threads. (d) With two undersize repair nuts, the part number of the nut being used must be stenciled on the nut as follows, UNDERSIZED STEERING NUT 8852949-01 (OR -03) INSTALLED, using a black polyurethane paint for the stencil.

I

I

(4) Identify reworked cylinder (80) by making an X after part number found on raised stamp pad on fulcrum, using an electric vibro etch tool. p. Cylinders (80) with flange bolts (54) holes, that are corroded or worn to 0.510 inch will be fl reamed oversized to 0.562510.5632 inch. Install bushing, part No. 9418192-01, using standard shrink-fit method. Apply wet sealant per Specification MIL-S-81733 to ID of holes prior to bushing installation. Final ream bushing ID to 0.50110.503 inch. q. Piston (16) with uplock link holes worn beyond 1.011 inch diameter will be reamed to 1.0661

T.O. 4S2-23-3

DIFFERENCE DATA SHEET

q.

Piston (16) holes inspection:

(1) Uplock link holes worn beyond 1.011inch diameter will be boredlreamed to 1.06611.067inch diameter. Locally manufacture bushing, length of 0.74510.749 inch, material 4340 steel per AMS-S5000, H.T. 260 to 280 ksi. TVD aluminum plate bushing Per Specification MIL-C-83488. Install bushing per T.O. 43-1-182. Line ream to 1.0061 1.009-inch diameter after installation. (2) Tow lug holes worn beyond 0.504-inch diameter will be boredlreamed to 0.56010.562-inch diameter. Locally manufacture bushing, material aluminum bronze per AMS 4590. Install bushing per T.O. 4s-1-182. Line ream to 0.50010.502-inch diameter aRer installation. NONDESTRUcTrVE IIlSPJ3CTION- Same as for part No. 7926487-10. LUBRICATION. Same as for part No. 371671-1, except as follows: a. Coat faying surfaces of shaft (65 and To), bolts (64 and 69), collar (55), bolts (581, bolts (7% spacer (74), and all O-rings with 0-Lube (Parker Seal Co, 10567 Jefferson Blvd, Culver City7 CA 90231).

b. On bearing (28) apply grease, Specification MIL-A-81322, a t assembly as follows: (1) coat liberally OD of bearing below O-ring and fill lightening grooves. (2) bearing.

coat sparingly

ID below 0+.ing in

(3) Coat mating surfaces of threads. c. Coat all mating surfaces of pin (75) and bushing (76) with grease, Specification MILG81322.

REASSEMBLY. (See Figure 6-7.) Reassemble shock strut assembly in reverse order of disassembly.

NOTE All bolts and fittings are to be torqued in accordance with T.O. 1-1A-8, unless otherwise specified.

a. Special Torque Values. Lower gland nut (15) is to be torqued to 90 to 110 foot-pounds and backed off to the nearest setscrew position. Crossbolts (64 and 69) are to be torqued to 700 to 800 inch-pounds. b. When installing shafts (65 and 70), ensure that spline tooth is on topside centerline of cylinder (80) and spline groove is on bottomside centerline. (See detail A, Figure 6-7.) c. Thinly coat inside of bushing bore, bushing flange faying surfaces, inside of crossbolt holes, and trunnion bore with STM40-112/Specification MILS-81733. Sealant to be tack-free prior to cleaning and painting operations. d. Separable seal flanged joint as follows: (1) Coat faying surface of collar (55) with low adhesion, corrosion-inhibiting sealant, part No. PR1403G (Courtaulds Aerospace Inc, 21800 Burbank Blvd, Third Floor, PO Box 4226, Woodland Hills, CA 91365-4226) or sealant per Specification MIL-S-81733, prior t o installation. (2) Coat faying surface of cylinder (80)with release agent, Plastilease 843 (Ram Chemical, 210 East Alondra Blvd, Gardena, CA 90248-2808). (3) Seal gland nut (15)to cylinder (80) joint and unused setscrew holes with a bead of inhibited polysulfide, part No. PR1422G (B2) (Courtaulds Aeros~ace). (4) Seal four flange bolts (54) to cylinder (80) and collar (55) with bead of sealant, Specification MIL-S-81733. TEST PROCEDURE. 363590-1A.

Same as for part No.

Change 5 6-39

T.O. 432-23-3

DIFFERENCE DATA SHEET

I

Figure 6-7. Nose Landing Gear Strut Assembly, Part Nos. 3303591-1 and 7926487-10, Exploded View (Sheet 1 of 2)

6-40 Change 2

T.O. 452-233

DIFFERENCE DATA SHEET

1. 2. 3. 4. 5. 6.

7. 8. 9. 10. 11. l2. 13. 14. 15. 16. 17. 18. 19. 20. 21. 22. 23. 24. 25. 26. 27.

VALVE O-RING STANDPIPE O-RING BOLT WASHER BOLT WASHER JACK PLUG NUT WASHER RETAINER BUSHING SETSCREW GLAND NUT PISTON COlTER PIN FLATHEAD PIN RETAINER BEARING RETAINER PIN CAM CAM KEY WASHER SEAL ASSEMBLY

28. 29. 30. 31. 32. 33. 34. 35. 36. 37. 38. 39. 40. 41. 42. 43. 44. 45. 46. 47. 48. 49. 50. 51. 52. 53. 54.

BEARING FELT STRIP SCRAPER BACKUP RlNG O-RING PACKING BACKUP RlNG BULKHEAD NUT ORIFICE SCREW LOWER PLATE UPPER PLATE NUT BOLT SCREW NUT BRACKET KEY FllllNG COLLAR BUSHING FITTING TAG SLEEVE NUT WASHER BOLT

55. 56. 57. 58. 59. 60. 61. 62. 63. 64. 65. 66. 67. 68. 69. 70. 71. 72. 73. 74. 75. 76. 77. 78. 79. 80.

COLLAR NUT WASHER BOLT FllTlNG BUSHING NUT WASHER WASHER BOLT SHAFT NUT BRACKET WASHER BOLT SHAR NUT WASHER BOLT SPACER PIN BUSHING FITTING NAMEPLATE NAMEPLATE CYLINDER

Figure 6-7. Nose Landing Gear Strut Assembly, Part Nos.3303591-1 and 7926487-10, Exploded View (Sheet 2 of 2)

Change 2 6-41/(6-42 blank)

T.O. 4S2-233

DIFFERENCE DATA SHEl3

NOSE LANDING GEAR STRUT ASSEMBLY

PART NO. 33035913,33142033, AND 3316500-13

THE INSTRUCTIONS CONTAINED IN PRECEDING SECTIONS OF THlS TECHNICAL MANUAL APPLY EXCEPT FOR THE DIFFERENCES LISTED IN THlS DATA SHEET

LEADING PARTICULARS. Same as for part No. 363590-14 except as follows:

.............................. ............................42.22 inches 2 5 1 pounds

SPECIAL TOOLS. PART NO. WR-341

NOMENCLATURE

Orifice Retaining

5120-00-6750833

Nut Wrench

DISASSEMBLY. (See figure 6-8.) Disassemble nose landing gear strut assembly in index number sequence assigned to exploded view. CLEANING. Same as for part No. 363590-1A INSPECTION. Same as for part No. 363590-1A except as follows: a. Substitute index numbers from figure 6-8 for similar parts in figure 6-4 and use table 6-6 for allowable service dimensions. b. If the strut assembly contains a cylinder assembly, part No. 3303590-7, the original diameters for holes in cylinder (82, figure 6-81, part No. 3303589-3, that hold shafts (67 and 72) are 2.43721 2.4383 inches; for cross-bolt holes that hold bolts (66 and 711, original diameters are 0.878010.8790 inch in both cylinder (82) and shafts (67 and 72). If the strut assembly contains a cylinder assembly, part No. 3303590-9 or 3303590-11, the original diameters for holes in cylinder (821, part No. 3303589-5, that hold shafts (67 and 72) are 2.635312.6342 inches; for cross-bolt holes that hold bolts (66 and

711, original diameters are 1.000011.0009 inches in both cylinder and shafts. For flange bolt holes that hold bolts (55), original diameters are 0.50110.508 inch in both cylinder and collar (56); for ID of the hole of collar that mates with cylinder, original diameter is 5.250315.2517 inches. c. Inspect all (new and used) cylinders (82) to ensure that bolts (66 and 71) have been identified with the letter P stamped on bolt head. If bolts do not have the letter P, they will be removed and processed per subparagraph j., Repair and Replacement. REPAIR AND REPLACEMENT. Same as part No. 363590-14 except as follows: NOTE

AU worn or corroded bolt holes shall be repaired in accordance with figure 6-9. a. Wear or damage exceeding table 6-6 and figure 6-9 shall be reworked. b. All machining operations shall be accomplished using floodcoolant techniques. Coolants, tooling, and operating techniques shall be consistent with state-of-the-art as relates to cutting, boring, reaming, honing, and milling steel products (4340) heat treated to 200 to 280 h i level. c. Shotpeen: Use No. 230 steel shot at 0.010 to 0.014 inch A2 intensity per Specification MILS13165. d. Substitute index numbers from figure 6-8 for similar parts in figure 6-3. e. Cylinder (82, figure 6-23) is 300M steel, heat treated to 280 to 300 h i . Shafts (67 and 72) are 4340 steel, heat treated to 200 to 220 ksi. Collar (56) is 300M steel, heat treated to 280 to 300 ksi.

Change 2 6-43

DIFFERENCE DATA SHEEl

Figure 6-8. Nose Landing Gear Strut Assembly, Part Nos. 3303591-3,3314203-3,and 3316500-13,Exploded View (Shed 1 of 2)

6-44

T.O. 4S2-23-3

DIFFERENCE DATA S H E n

1. VALVE 2. O-RING 3. STANDPIPE 4. O-RING 5. BOLT 6. WASHER 7. BOLT 8. WASHER 9. JACK PLUG 10. NUT l l . WASHER 12. RETAINER 13. BUSHING 14. SEXCREW 15. GLAND NUT 16. PISTON 17. COllER PIN 18. FLATHEAD PIN 19. RETAINER 20. BEARING 21. RETAINER 22. PIN 23. CAM 24. CAM 25. KEY 26. WASHER 27. SEAL ASSEMBLY 28. BEARING 29. FElT STRIP 30. SCRAPER 31. BACKUP RlNG 32. O-RING PACKING

33. 34. 35. 36. 37. 38. 39. 40. 41. 42. 43. 44. 45. 46. 47. 48. 49. 50. 51. 52. 53. 54. 55. 56. 57. 58. 59. 60. 61. 62.

BACKUP RlNG BULKHEAD NUT ORIFICE SCREW LOWER PLATE UPPER PLATE NUT BOLT SCREW NUT BRACKET K N FIRING COLLAR BUSHING FIRING TAG SLEEVE RlNG NUT WASHER BOLT COLLAR NUT WASHER BOLT FITTING BUSHING O-RING (33035967 CYLINDER ONLY)

63. 64. 65. 66. 67. 68. 69. 70. 71. 72. 73. 74. 75. 76. 77. 78. 79. 80. 81. 82. 83. 84. 85. 86. 87. 88. 89. 90. 91. 92.

NUT WASHER WASHER BOLT SHAR NUT BRACKET WASHER BOLT SHAR NUT WASHER BOLT SPACER PIN BUSHING FITTING NAMEPLATE NAMEPLATE CYLINDER BUSHING BUSHING FITTING (USED WITH SHAFI, PART NO. 3314207-5) CLAMP BLOCK SCRRN COTTER PIN NUT WASHER BOLT MOUNT

Figure 6-8. Nose Landing Gear Strut Assembly, Part Nos. 3303591-3, 3314203-3, and 3316500-13, Exploded View (Sheet 2 of 2)

Table 6-6. Allowable Service Dimensions REPAIR DIMENSIONS PART NO.

AND LOCATION (See figure S 8 ) Outer Cylinder Drag Pin Hole

Bushing (78)

Bushing (78)

Drag Brace Pin (77)

Bracket (44)

Actuator Attach Lugs

Bushings (61)

Bushings (61)

Steer Cylinder Attach Lugs Cylinder Trunnion (82)

ORIGINAL DIAMETER MIN

D

MACH OVERSIZE

68D29135-43

63

0.006

68D29135-43

100

0.005

68D29135-43

100

MIN

MAX

MIN

MAX

0.0002

0.003

-

1.7530

0.006

1.7470

1.565

1.7500

1.7519

ID

ID

1.7489 OD

1.7498 OD

0.0002

0.003

0.0003

0.002

0.0003

0.002

1.5625

1.5635

ID

1.5615 OD

1.5623 OD

1.3745

1.3750

ID

ID

PLATING REPAIR OR REPLACEMENT PART

MACH FINISH

MAX

1.3073

0.0007

0.0019

0.06243

0.0007

0.0014

1.1898 OD

68D29135-33

125

1.066

68D29135-33

125

0.503

68D29135-51

63

0.5000

0.5010

2.4372

2.4383

ID

ID

2.436 OD

2.437 OD

0.0047

*

0.003 Loose Fit

0.0019

1.1890 OD

1.0634

0.0002 Loose Fit

0.0007

63

ID

1.8702

1.5993

68D29135-33

1.0625

MAX

63

1.1885

ID

MIN

68D29135-49

m

1.1875

BUSHING INTERFERENCE

100

0.005

1.560

ID

0.0002 Trunnion Shaft (67 and 72)

MAX

CLEARANCE

CLEARANCE

ID

REWORK LIMITS

SERVICE TOLERANCE

Table 6-6. Allowable Service Dimenswns (Cont)

PART NO.

AND LOCATION (See figure 6-8)

ORIGINAL DIAMETER MIN

MAX

Cylinder Crossbolt Hole D

0.8780

0.8790

ID

ID

Bolt (71) D

0.8730

0.8740

OD

OD

Trunnion Shaft Bolt Hole

0.8780

0.8790

ID

ID

Bolt (66 and 71)

0.8730

0.8740

OD

OD

2.6342

2.6353

ID

ID

Bushing (83)

2.6360

2.6372

OD

OD

CLEARANCE MIN

MAX

0.0040

0.0060

Trunnion Shaft (67 and 72)

-

2.4372

0.0060

2.4383

m

ID

2.436

2.437

OD

OD

Cylinder Crossbolt Hole D

1.0000

1.0009

ID

ID

Bushing (84)

1.0009

1.0014

OD

OD

DIAMETER

MIN

MAX

MAX CLEARANCE

REPAIR OR REPLACEMENT PART

STSBGOOlA14U064

(-)0.0030 (-)0.0007

Bushing (83)

BUSHING

PLATING

I3

0.0040

Cylinder (82) Trunnion

REWORK LIMITS

SERVICE TOLERANCE

REPAIR DIMENSIONS

0.0002

0.0047

(-)0.0014

0.0000

MACH FINISH

MACH OVERSIZE

INTERFERENCE

MIN

MAX

Table 6-6. Allowable Seruice Dimensions (Cont)

PART NO. AND LOCATION (See figure 68) Bushing (84) Bolt (66 and 71)D

ORIGINAL DIAMETER

MIN

MAX

0.8780

0.8790

ID

ID

0.8730 OD

0.8740

D CLEARANCE MIN

MAX

0.0040

0.0060

MIN

OD

A minus (-1 in front of the clearance signifies an interference fit. Cylinder, part No. 3303589-3(without bushings). Cylinder, part No. 3303589-5(with bushings).

REWORK LIMITS

SERVICE TOLERANCE

REPAIR DIMENSIONS

MAX

MAX CLEARANCE

PLATING REPAIR OR REPLACEMENT

PART

MACH FINISH

MACH OVERSIZE

BUSHING INTERFERENCE

MIN

MAX

T.O. 4S2-23-3

DIFFERENCE DATA SHEm

E m ON ONE-PIECE OUTER CYLINDERS, PART NO. 3303590.1, THE FOLLOWING DIMENSIONS APPLY ON ACTUATOR FACE-TO-FACE BASE METAL 1.210 (20.010) INCHES BUSH ING FLANGE -0.050 INCH, AND FACE-TOFACEWITH BUSHING 1.1 10 (20.010) INCHES.

A.

:=.l

t

'0:

THD 5 114-16LJH-

D + & =

\

1 4.7.7 1

Figure 6 9 . Replacement and Reconditioniw Dimensions (Sheet 1 of 3)

5 1/8-16UNS-3A

PITCH DIA

T.O. 4S2-233

DlfTERENCE DATA SHEET.

ACCEPTABLE TO REMOVE UP TO 0.020 INCH MATERWJ SIDE EITHER LOCAUY OR ENTIRE AREA FROM DIMENSIONS SHOWN ON ORIOINAL BLUEPRINTSHOW= REWORKED AREA. (BELOW STEP SEALTO PISTON BOTTOM)

I

EITHER REMOVE

2 7116-16N3A

0 PISTON AND AXLE

(ROTATED 900 CW)

Figure 6 9 . Replocement and Reconditioning Dimensions (Sheet 2 of 3)

650 Change 1

OR ENnRE AREA SHOTPEEN REWORKEDAREAS.

T.O. 4S2-233

DIFFERENCE DATA SHEET

DIA W P )

1.0009 DIA

WP)

DIMENSIONS SHOWN ARE AFTER TlTANlUM CADMIUM PLAnNG AS PER MIL-STD-1500, CLASS 2. G9500251

NOTE

AFI'ER MACHINING CYLINDER, PART NO. 3303589-3, TO THESE DIMENSIONS, REIDENTIFY CYLINDER AS PART NO. 3303589-5.

Figure 6 9 . Replacement and Reconditioning Dimensions (Sheet 3 of 3)

Provide adequate ventilation during cadmium plating. Wear protective gloves and chemical goggledface shield to prevent skin and eye contact. The local bioenvironmental engineer will provide information regarding specific respiratory and personal protective equipment requirements.

f. Vacuum cadmium plate the exterior surfaces of cylinder (82) except those surfaces that mate with collar (56). There is no maximum thickness on exterior surfaces except 0.0003 inch thickness on threads.

Provide adequate ventilation during cadmium plating. Wear protective gloves and chemical goggledface shield to prevent skin and eye contact. The local bioenvironmental engineer will provide information regarding specific respiratory and personal protective equi$ment >eq&ments. g. Vacuum cadmium plate the 4.75014.752-inch interior surface (figure 6-9) to a thickness of 0.0001510.0006 inch.

T.O. 4S2-23-3

DIFFERENCE DATA SHEET

respiratory and personal protective equipment requirements. Provide adequate ventilation during cadmium plating. Wear protective gloves and chemical goggleslface shield to prevent skin and eye contact. The local bioenvironmental engineer will provide information regarding specific respiratory and personal protective equipment requirements. h. Collar assembly (56, figure 6-8), part Nos. 3303583-11-5: (1) Remove corrosion and pitting on ID by grindinglmachining to maximllm of 5.2667 inches and chrome plate ID per MIL-STD-1501, Type 11, Class 3. Finish grinding ID to final dimension of 5.250315.2517 inches. (2) If corrosion still remains after grinding ID at 5.2667 inches, grind ID to maximum of 5.2850 inches for flame spray repair per MIL-STD-869 using METCO 451 material. Sulfaxnate nickel plating per MIL-STD-686 may be used as an alternate method. Finish grinding ID to final dimension of 5.250315.2517 inches. (3) If collar bolt (55) holes are corroded or worn to 0.510 inch, oversize hole to 0.5625/0.5632 inch. Install bushing, part No. 9418192-01, using standard shrink-fit method. Apply wet sealant per Specification MIL-S-81733 to ID of holes prior to bushing installation. Final ream bushing ID to 0.50110.503 inch. (4) Remove corrosion from the entire plane surface area of collar assembly (areas adjacent to 5.2517-inch bore) by grinding either or both surfaces. The 2.750 inch face-to-face thickness will not be reduced below 2.720 inches during grinding. Chrome plate face-to-face per MIL-STD-1501, Type 11, Class 3, and finish grinding to 2.74012.760 inches. Sulfamate nickel plating per MIL-STD-868 may be used as an alternate method.

Provide adequate ventilation during cadmium plating. Wear protective gloves and chemical goggledface shield to prevent skin and eye contact. The local bioenvironmental engineer will provide information regarding specific

6 5 2 Change 2

i. Chrome plate surfaces of cylinder (82) that mate with collar (56) per MIL-sTb-1501, Type 11, Class 3. Plah (Type I) the lower surface of bolt flange 0.00Y0.0025-inch thick. Plate (Type II) the cylinder wall that mates with collar (56) to after plating diameter of 5.2484.15.2498 inches. Maximum plating thickness is 0.0075 inch. j. Rework of shafts (67 and 721, part Nos. 3314207-1, -3, and -5.

All shotpeening, grinding, and abrasive blasting operations must be performed in an adequately ventilated booth. The local bioenvironmental engineer will provide information regarding specific respiratory and personal protective equipment requirements. (1) Damagelcorrosion may be removed fmm particular areas by grinding per MILSTD-866 to the following dimensions: (a) 2.437-inch diameter; grind to 2.422 inches millimum. (b) 1.8748-inch diameter; grind to 1.860 inches minimum. NOTE

Remove only material required to clean up. (2) Nital etch per MIL-STD-867. (3) Chrome plate ground areas to sizes noted per MU,-STD-1501, Type 11, Class 3. (a) 2.422-inch minimum diameter; plate to 2.43712.436-inch diameter; 63 RMS finish.

(b) 1.860-inch minimum diameter; plate to 1.874811.8739-inch diameter; 63 RMS finish (4) Radius toward splined area on 1.8748inch diameter to be 0.12 (f0.03) inch. (5) Chrome plate may run out on side of 0.1910.22-inch diameter relief cut. (6) Chrome plate may run out on 0.0610.09 inch radius of 2.437-inch diameter.

I

/

i~

T.O. 4S2-233

DIFFERENCE DATA SHEET

I

Provide adequate ventilation during cadmium plating. Wear protective gloves and chemical goggledface shield to prevent skin and eye contact. Local bioenvironmental engineer will provide information regarding specific respiratory and personal protective equipment requirements. (7) Cadmium plate threads and splines per Specification MIL-C-8837, Type I, 0.003-inch thick; cadmium plate all other surfaces per Specification MIL-C-8837, Type I, Class 1. (8) Crossbolt holes worn to a maximum diameter of 0.882 inch will be chrome plated back to size per MIL-STD-865. Finish dimension is 0.8791 0.878 inch. (9) Holes which cannot be repaired per subparagraph (8) will be oversized to 0.937510.9380inch diameter. Install bushing, part No. 893025305, on shaft, part No. 3314207-5, and bushing, part No. 8930253-03, on shaft part Nos. 3314207-1 and 3. k. Repair of pulley mounting lug is not applicable. Lug is a removable eyebolt on these assemblies. Repairs to firlcrum are not applicable on these assemblies. 1. Rework of through holes in trunnion of outer cylinder: NOTE Cylinders, part No. 3303589-3, that are required by subparagraph (1)must incorporate all of the repairlrework in figure 6-9. Subsequent to this repair1 rework, reidentify cylinders to part No. 3303589-5. (1) If reworking outer cylinder, part No. 3303589-3, trunnion through holes worn to a maximum diameter of 0.882 inch will be machined to dimensions shown in figure 6-9. Shaft holes and trunnion must also be machined to the dimensions shown in figure 6-9 and bushings (83 and 84, figure 6-8) installed. For outer cylinder, part No. 3303589-5, replace through hole bushing (84) if bushing ID exceeds 0.882 inch. To install bushings, follow these procedures:

Provide adequate ventilation when using dry ice and alcohol. Wear protective gloves and prevent skin contact. Do not ingest. Failure to observe safety precautions could result in personal injury or death. (a) Prior to bushing installation, clean parts and bore with aliphatic naphtha, Federal Specification TT-N-95, or equivalent, and apply coat of STM40-112 (Courtadds Aerospace h c , Part No. PR-1431G, Type I, 21800 Burbank Blvd, 3rd Floor, PO Box 4226, Woodland Hills, CA 913654226) to ID of crossbolt of shaft holes. Allow to dry for 12 hours. (b) Subzero install bushing using dry ice and alcohol. (c) Fillet seal both ends of bushing with sealant, ST.40-111, Class B-112 (Courtaulds Aerospace Inc, Part No. PR-1422G, B-112, same address as above) to be tack-he prior to cleaning or painting operations.

Eye protection must be worn while involved in reaming operations. Also, adequate ventilation must be provided when using sealing compound. Avoid prolonged or repeated skin contact. (2) After installing bushing (84), ream 0.87910.878 diameter holes in line through bushings before installing fasteners or shaft. Only install shaft (67 and 72, figure 6-8, part No. 3314207-5) with grease fitting, part No. MS15001-1, after bushing installation on either part number outer cylinder.

Provide adequate ventilation during plating operations. Provisions of AFOSH Standards 161-1, 161-2, and 127-31 will be strictly adhered to regarding adequacy of respiratory protection, ventilation, and personal protective clothing and equipment.

Change 2 6-53

T.O. 4S2-23-3

DIFFERENCE DATA S H E n

m. Rework of through bolts (66 and 71). All bolts not identified with the letter P on head will have bolt grip plated to a diameter of 0.877510.8770 inch. Plating may be chrome plate per MIL-STD1501, Type I or 11, Class 3, electroless nickel per Specification MIL-C-1607, Class 2, Grade C; maintain a 32 RMS surface finish. Plating may fade out 1/16 inch from head and ll16 inch fkom thread relief radius. Impression stamp or vibro etch letter P, ll4inch high letters, at approximate center of bolt head after plating.

Eye protection must be worn while involved in reaming and drilling operations. Also. adeauate ventilation must be provided when using sealing compound. Avoid prolonged or repeated skin contact. NOTE

Cylinders, part No. 3303589-3, that are repaired by subparagraph n. must incorporate all of the repairlrework in figure 69. Subsequent to this repair1 rework, reiden* cylinders to part No. 3303589-5. n. Rework of hole for shafts (67 and 72, figure 6-8). If reworking outer cylinder, part No. 3303589-3, shaft holes worn beyond 2.439-inch diameter will be machined to dimensions shown in figure 6-9 and bushings installed. Trunnion through holes, shaft holes, and trunnion must also be machined to the dimensions of figure 6-9 and bushings installed. For outer cylinder, part No. 3303589-5, replace shaft hole bushing if bushing ID exceeds 2.439 inches. To replace bushings, follow instructions given in subparagraphs l.(lXa) through (c). . .

All abrasive blasting operations shall be performed in an adequately ventilated booth. Local bioenvironmental engineer will provide information regarding specific respiratory and personal protective equipment requirements.

6-54 Change 2

Provide adequate ventilation during cadmium plating. Wear protective gloves and chemical goggledface shield to prevent skiin and eye contact. Local bioenvironmental engineer will provide information regarding specific respiratory and personal protective equipment requirements. o. Threaded area at lower end of steering collar area. Shallow corrosion to a maximum depth of 0.006 inch over entire surface may be grit blasted per MIL-STD-1504. Cadmium plate threads per Specification MIL-C-8837, Type I, 0.0003 inch thick.

Provide adequate ventilation when using dry film lubricant. Wear protective gloves and prevent skin contact. Do not ingest. p. Treat threaded areas and keyways with dry film lubricant 5305 applied over cadmium plated surfaces. Overspray permissible; air-dry to cure. No post bake is required. q. Cylinders (82) with corroded lower gland nut threads may have new threads ground and undersize gland nut (15) installed. New threads should be 5.090-16UNS-3& major diameter equals 5.090015.0806, pitch diameter equals 5.049415.0437, minor diameter equals 5.013315.0088. (1) Nital etch per MIL-STD-867. (2) Bake for four hours at 375 (st25I0F within four hours after grinding. (3) Vacuum cadmium plate per Specification MILC-8837, Type 11, 0.0003-inch maximum thickness on threads. (4) Undersize gland nut (15), part No. 8852955, should be used with this repaired cylinder. Stencil on the nut, using black polyurethane paint, UNDERSIZED GLAND NUT I N S T U D .

r. Cylinders (82) with corroded steering mounting plate nut threads may have new threads ground and undersize nut (43) installed. (1) The first undersize repair will have new thread 5.220-16UN-3A, major diameter equals 5.22015.2106, pitch diameter equals 5.1794/5.1737, minor diameter equals 5.143315.1388. Undersize

,

1

T.O. 4S2-233

DlFFERENCE DATA SHEET

nut (431, part No. 8852949-01, should be used with this repaired cylinder. (2) The second undersize repair will have new thread 5.185-16UN-3A, major diameter equals 5.185015.1756, pitch diameter equals 5.144415.1387, minor diameter equals 5.108315.1038. Thread relief groove above threads must be recut to 5.09015.095 diameter. Undersize nut (431, part No. 8852949-03, should be used with this repaired cylinder. (3) After either repair, the following processing must be accomplished: (a) Nital etch per MIL-STD-867. (b) Bake for four hours at 375 (+251OF within four hours after grinding. (c) Vacuum cadmium plate per Specification MIL-C-8837, Type 11, 0.0003-inch maximum thickness on threads. (dl With two undersize repair nuts, the part number of the nut being used must be stenciled on the nut as follows, UNDERSIZED STEERING NUT, PART NO. 8852949-01 (OR -03) I N S T W D . Use a black polyurethane paint for the stencil. (4) Identi@reworked cylinder (82) by making an X after part number found on raised stamp pad on fulcrum using an electric vibro etch tool. s. PistonIAxle Assembly (151, Part No. 380204-5. (1) Vacuum cadmium plate all external surfaces not chrome plated, including lugs, lug IDS, and bearing areas. Plate ID of axle. Plating on ID of piston is optional (figure 2-31. (2) Locally polish minor blemishes in the chromium plate within 3.993-inch diameter. (3) If plated surface is worn beyond tolerance or damaged, recondition as follows: (a) Strip chromium plate. (b) Grind to a 3.980-inch maximum, remove defects, and polish the 0.500-inch radius below the chromium plate to a 32 RMS or better finish. Maintain a minimum wall of 0.155 inch. (c) Bake. (d) Shotpeen. (el Chromium plate. ( f l Bake.

I

(g) Grind to 3.995313.9975-inch diameter, diameter to be concentric within 0.002 TIR. (4) Inspect the wheel bearing journals of the axle for wear, scoring, galls, and pits. (a) On the outer bearing journals, minor blemishes may be locally polished provided: 1 No more than 20 percent of the bearing area is affected by the polishing. 2 Depth of the polishing does not exceed 0.03G inch. (b) On the inner bearing journals, minor blemishes may be locally polished provided: 1 No more than 10 percent of the bearing area is affected by polishing to a depth not to exceed 0.010 inch. 2 No pit edge is sharper than 0.060 radius. 3 No more than 30 percent of any one square inch-of area is affected by polishing. (c) If damage is more extensive: 1 Grind the inner journals sufficiently to remove afects not to exceed 0.015-inch material removal on the diameter maintaining 0.120-inch maximllm wall thickness. 2 Grind the outer journals to remove defects not% exceed 0.020 inch minimum outer diameter. If defects remain, locally hand polish not to exceed 10 percent of the journal area. 3 Bake. -

Nital etch inspection must be accomplished by qualified personnel only. -4 Nital etch inspect. 5 Bake. 6 Shotpeen. -7 Chrome plate. -8 Bake. 9 Grind inner journals to 2.99981 2.9990-inch-iliameter and outer journals to 2.49901 2.4998-inch diameter. 10 Bake. -

Change 2 G55

T.O. 4S2-23-3

DIFFERENCE DATA SHEET

(O

Provide adequate ventilation during f luorescent-penetrant inspection. Wear protective gloves and prevent skin contact with solution and developer. 11 Magnetic-particle inspect per Specification -1-6868C. t. Steering collar sleeve (48, figure 6-4), part No. 340876. (1) If not previously accomplished, rework keyway slot depth to 0.625-inch maximum to obtain an 0.09010.110-inch radius in corners. (2) If cracks are evident in keyway corner and do not exceed 1/32 inch in depth, smooth and blend in with radius. u. Steering collar (44) part No. 352604. (1) Remove corrosion h m inside diameter by locally polishing or grinding sufficiently to remove defects but not to exceed 0.030 inch in depth o r 35 percent of surface area. Maintain a finish of 32 RMS surface roughness with a minimum radius of 0.500 inch blending reworked area into parent metal. (a) Shotpeen reworked surface using No. 230 steel shot at 0.010 to 0.014 4 intensity per Specification MIL-S-13165. Fade shotpeening on surfaces adjacent to reworked areas. (b) Bake for four hours at 375 (f25)OF. (2) If corrosion cannot be removed in accordance with subparagraph (11, grind inside diameter oversize 0.030 inch in accordance with MIL-STD866. (a) Isolated pits remaining after grind shall be removed by locally polishing to a depth of 0.020 inch. (b) Shotpeen inside diameter of collar using No. 230 steel shot at an 0.010 to 0.014 A2 intensity. (c) Bake for four hours at 375 (f25)OF prior to plating. (dl Electroless nickel plate inside diameter of the collar per Specification MILC-26074. (e) Grind to 5.500015.5014 per MILSTD-866.

856 Change 2

Bake for four hours a t 375 (f25)'F: v. Gland nut (14). Drill two 0.1250 (+0.0015/ -0.0000) inch diameter holes, 180 degrees apart and 0.387 inch above bottom face of gland nut (14). Install lubrication fitting NAS-516-1 in each hole. w. Steering bracket (411, part No. 355845-1. (1) Grind inside diameter of steering bracket to remove corrosion but not to exceed 5.272 inches. Locally polish isolated pits, as required, up to 0.040-inch depth maximum not to exceed 30 percent of circumference. Remove corrosion on flat surface by locally polishing or air blasting with aluminum oxide grit or suitable substitute until corrosion products are removed. Corrosion removal shall be limited to 45 percent of surface area and 0.030-inch maximum depth. (2) Electroless nickel plate ID and grind to 5.25015.252 inches in accordance with Specifications MILC-26074 and hIIL-STD-866. (3) Corrosion and other defects on ID of 1.374511.3750-inch steering cylinder hole may be removed to an ID of 1.5993 inches. The 1.170-inch diameter opening a t bottom of this hole should not be enlarged. Walls of reworked portion of hole should be blended with bottom of hole using a 0.0101 0.030 inch fillet radius. Chamfer of OD of the 68D29135-49 bushing shall be increased to 45 degrees by 0.03010.035 inch NONDESTRUCTION INSPECTION. Same as for part No. 363590-1A except as follows: a. NLG cylinder assembly (82, figure 6-8) is made of 300M steel, heat treated to 280 to 300 ksi. b. Inspect cylinder as follows: Table 6 7 . Circular Magnetization CONDUC-

FIGURE 6-8 INDEXNO. 82

TOR PART

NAME Cylinder Assembly

POSITION NO.

CURRENT

1 (Central Conductor)

1000 AMPS

2 (Head Shot)

2000 AMPS

3 (Head Shot)

2000 AMPS

,

T.O. 4S2-23-3

DIFFERENCE DATA S H E n Table 6-8. Longitudinal Magnetization

FIGURE 6-8

INDEX NO. 82

PART NAME

COIL LOCATION NO.

Cylinder Assembly

A-1, A-2 (figure 6-10)

1500 AMPS with &turn coil (7500 AMP turns)

B-1, B-2 (figure 610)

1500 AMPS with 5-turn coil (7500 AMP turns)

CURRENT

Change 2 6-56A/(S56B blank)

T.O. 4S2-233

DIFFERENCE DATA SHEET 2

Figure 6-10. Cylinder Assembly Inspection Coil b a t i o n and Conductor Position, Part Nos. 33035893 and 3303589-5

LUBRICATION. Before reassembly, coat entire interior of strut cylinder and exterior of piston with hydraulic fluid, Specification MIL-H-5606. In addition, presoak all packings in hydraulic fluid, Specification MIL-H-5606, before installation andlor assembly. Lubricate pressure lubrication points with grease, Specification MIEG-81322. a. Coat faying surfaces of shaft (67 and 72, figure 6-81, bolts (66 and 711, collar (561, bolts (59 and 751, spacer (76), and all O-rings with grease, Specification MIL-G81322. b. On bearings (28) apply grease, Specification MIL-A-81322, at assembly a s follows: (1) Coat liberally OD of bearing below O-ring and fill lightening grooves.

(2) Coat sp-gly 1 ' below O-ring in bearing. (3) Coat mating surfaces of threads. c. Coat mating surface of pin (77) and bushing (78) with grease, Specification MIL-G81322.

REASSEMBLY. (See figure 6-8.) Reassemble shock strut assembly in reverse order of disassembly. NOTE

All bolts and fittings are to be torqued in accordance with T.O. 1-1A-8 unless otherwise specified. a. Special Torque Values. Lower gland nut (15, figure 681, part No. 373517-7, is to be torqued to 90 to 110 foot-pounds and backed off to the nearest setscrew position. Crossbolt (66 and 7 1)are to be torqued to 700 to 800 inch-pounds. b. When installing shafts (67 and 72). ensure that spline tooth is on topside centerline of [cylinder (82) and spline groove is on bottom side centerline. (See fiwe Cs.) c. Thinly coat inside of bushing bore and bushing flange faying surfaces with SI"I'40-112/S~ecification IifIL~81733prior to installation of bishing, then fillet seal both ends of bushing with STM4O-

DIFFERENCE DATA S H E n

lll1Specification MIL-S-81733. Sealant to be tackfree prior to cleaning and painting operations. d. Thinly coat inside of crossbolt holes and trunnion bore -with SW4O-112/Specification MILS-81733 prior to installation of bushing, then fillet seal both ends of bushing with STM40-111/Specification MIL-S-81733. Sealant to be tack-free prior to cleaning and painting operations. e. Separable seal flanged joint as follows: (1) Coat faying surflzce of collar assembly, part No. 3303583-5, with low adhesion corrosioninhibiting sealant, part No. PR1403G (Courtadds Aerospace Inc, 21800 Burbank Blvd, 3rd Floor, PO Box 4226, Woodland Hills, CA 91365-42261, prior to installation. (2) coat faying surface of cylinder flange, part No. 3303589-5 with release agent, Plastilease 843 (RAM Chemicals, 210 E Alondra Blvd. Gardena, CA 90248-2808).

6-58 Change 2

f. Seal gland nut (15) to cylinder (82)joint and unused setscrew holes with a bead of inhibited polysulfide, part No. PR1422G (B2) (Courtadds Aerospace Inc, s m e address as subparagraph e-(1)). g. Seal collar bolt for part No. 3303590-7 with bead of sealant, Specification MIL-S-81733. h. Install filler, part No. 367643-1, to collar (56) using chlorophrene base cement or 3M Scotch grip 1300L rubber and gasket adhesive. Surface shall be wiped dry with a clean cloth saturated with aliphatic naphtha per Federal Specification TT-N95, or trichloroethane per Federal Specification 0-T-620, or cleaning solvent per Federal Specification P-D-680. Location of filler is identified on drawing - No. 3303583. TEST PROCEDURE. Same as for pa* p ~ ~ 363590-1A

T.O. 4S2-23-3

DIFFERENCE DATA SHEET

PART NO. 9235508-10

NOSE LANDING GEAR STRUT ASSEMBLY

THE INSTRUCTIONS CONTAINED IN PRECEDING SECTIONS OF THlS TECHNICAL MANUAL APPLY EXCEPT FOR THE DIFFERENCES LISTED IN THlS DATA SHEET

LEADING PARTICULARS. Same as for part No. 3314203-3 except for as follows: Replace bracket, part No. 380222-3, with part No. 9235338-01. Replace extension shaft, part No. 380246-1, with part No. 9235339-01. MODIFICATION OF PISTON ASSEMBLY, PART NO. 388028-19. If is ton assemblv. art No. 9235340-10 is not ava'ilable. modification of ist ton assembly, part No. 388028-19 is authorized w;th the following exception. d

7

L

a. Plug existing uplock link attach holes with plugs manufactured from 4340 steel heat treated to 200 to 220 ksi. OD of plugs to be such to ascertain a n interference fit of 0.001 to 0.002 inch diameterally. Plug length to be equal to or 0.005 inch less than lug length. b. Brush cad plate per MIL-STD-865 plug ODs prior to installation.

d. Bore and ream ski bracket attach holes to meet all dimensional and finish demands of Air Force dwg, part No. 9235340-10 (98747). e. Complete modification of piston assembly, part No. 388028-19 to piston assembly, part No. 9235340-10 by accomplishing all dimensional and finish demands of Air Force dwg 9235340-10 (98747). f. Do not paint piston axle ID and axle cross bolt holes ID. REWORK OF AXLE CROSS BOLT HOLES. Axle cross bolt holes that do not exceed 0.504 inch in wear may be used as is. Wear andlor damage that exceeds 0.504 inch shall be machined oversize to 0.560 to 0.561 inch with finish of 123 rms. Temper etch per existing directive. Locally manufacture oversized bushing from 4340 steel, heat treated to 260 to 280 ksi. Install bushing using bushing installation procedures specified by T.O. 48-1-182. Final ream busing ID to 0.500 to 0.501 inch.

c. Install plugs using bushing installation procedures specified by T.O. 43-1-182.

Change 6 6-59/(6-60 blank)

T.O. 4S2-233

DIFFERENCE DATA SHEET

NOSE LANDING GEAR LOWER TORQUE ARM ASSEMBLY NOSE LANDING GEAR UPPER TORQUE ARM ASSEMBLY

PART NO. 388068-1 PART NO. 388069-1

THE INSTRUCTIONS CONTAINED IN PRECEDING SECTIONS OF THlS TECHNICAL MANUAL APPLY EXCEPT FOR THE DIFFERENCES LISTED IN THlS DATA SHEET

INSTALLATION OF BUSHINGS IN TORQUE ARMS. Same as for part Nos. 355205-1 and 355117-1, except in figure 2-8 change note 12> to read:

Machine to 1.400 to 1.398 after installation of bushings.

6-61/(6-62

blank)

T.O. 4 S 2 - 2 3 3

DIFFERENCE DATA SHEET

NOSE LANDING GEAR ASSEMBLY (USING STRUT ASSEMBLY, PART NO. 364653-2A

PART NO. 39617511

THE INSTRUCTIONS CONTAINED IN PRECEDING SECTIONS OF M I S TECHNICAL MANUAL APPLY EXCEPT FOR THE DIFFERENCES LISTED IN THIS DATA SHEET

BUILDUP INSTRUCTIONS. Same as for part No. 396175-13, except as follows: In figure 5-1, index numbers for sheet 1 are changed as follows: 1. 364653-2A STRUT ASSEMBLY 5. 351519 RETAIMER (2 REQD) 6. BLN12003G-C BEARING (4 REQD) lo. NAS430012-2 SPACER (4 REQD)

13. 351517 SEAL (2 REQD) SUBASSEMBLY BUILDUP. Same as for part No. 396175-13, except as follows: In figure 5-2, index numbers are changed a s follows: 2. 337387 VALVE (2 REQD) 4. 356304-1 RETAINER (2 REQD)

11. 695548-3 STEERING CYLINDER (2 REQD)

6-63/(6-64 blank)

DIFFERENCE DATA SHEET

PART NO. 39617517

NOSE LANDING GEAR ASSEMBLY (USING STRUT A S SEMBLY, PART NOS. 371671-1,7926486-10, AND 7926486-30)

THE INSTRUCTIONS CONTAINED IN PRECEDING SECTIONS OF THlS TECHNICAL MANUAL APPLY EXCEPT FOR THE DIFFERENCES LISTED IN THIS DATA SHEET

BUILDUP INSTRUCTIONS. Same as for part No. 396175-13, except as follows: a. In figure 5-1: Sheet 1, index numbers are changed as follows: 1. 371671-1 STRUT ASSEMBLY 4. AN7502-28 NUT (2 REQD) Sheet 2, index numbers are changed as follows: 23. MS20392-3-49 PIN 25. AN381-2-9 COTTER PIN 27. MANIFOLD ASSEMBLY (BUILT UP ON 372683-1, SEE FIGURE 6-12) 31. NOT USED 32. NOT USED 33. MANIFOLD ASSEMBLY (BUILT UP ON 372684-1, SEE F I G m E 6-12) Sheet 3 is replaced by figure 6-11, sheet 1. Sheet 5, index numbers are changed as follows: 76. 396175-25 AND TUBING ASSEMBLY 77. 371670-1 BOLT

139. NAS1197-10 WASHER (2 REQD, UNDER BOLT HEAD) AN960ClOL WASHER (2 REQD, UNDER NUT) Sheet 9, index numbers are changed as follows: 161. 339242-4 WHEEL AND TIRE ASSEMBLY (2 REQD) 167. MS21902-6 UNION (PART OF 76) 168. MS21908-6 ELBOW (2 REQD, PART OF 76) b. In instructions: (1) Omit subparagraphs (26) and (27). (2) Replace subparagraphs (38) through (42) with new subparagraphs (38) through (42):

78, 372667-1 WASHER 82. 371689-1R BRACE ASSEMBLY

((38)) Install four gaskets (46) on four unions (47) and lubricate with petrolatum, Federal Specification W-P-236. ((39)) Install two of the unions (47) in each of the steering cylinders (11). ((40)) Lubricate the threads of the four unions on the inboard sides of manifold assemblies (27) and (33). ((41)) Install hose assembly (48) and tighten fittings. ((42)) Install hose assembly (51) and tighten fittings. (3) Replace the note preceding subparagraph (58) with the following note and subparagraph (57A):

83. 371689-1L BRACE ASSEMBLY

NOTE

84. 756001-1 SPACER (2 REQD) 85. NAS1022A17 NUT (2 REQD) Sheet 6 is replaced by figure 6-11, sheet 2. Sheet 7, index No. 139 is changed as follows:

.

Perform subparagraphs (57A) through (60A) only if a new arm (90) and/or arm (93) is being installed. ((57A)) Remove screws holding jack plug (88) to the bottom of strut assembly (1). Remove jack plug.

T.O. 4S2-23-3

DIFFERENCE DATA S H E n (4) Add subparagraph (60A) following subparagraph (60):

(3) Replace subparagraphs (24) through (27) with new subparagraphs (24) and (25):

((60A)) Replace jack plug (88) and screws removed in subparagraph (57A). Tighten the screws and safetywire using lockwire, part No. MS20995C32.

(24) Install two gaskets (24) on two unions (25) and lubricate with petrolatum, Federal Specification W-P-236.

(5) Replace subparagraph (69) with new subparagraphs (69) and (69A): ((69)) Install crossbar (115) and shims (119) in arms (90 and 93). Peel laminations of shim to fit; the maximum allowable gap is 0.005 inch. When the correct shim thickness has been determined, paint the shims with zinc chromate primer, Federal Specification TT-P-1757. ((69A)) Secure the crossbar (115) and shims (119) in position with four bolts (120) and nuts (122). Tighten the nuts. SUBASSEMBLY BUILDUP. Same as for part No. 396175-13, except a s follows: a.

Figure 5-2 is replaced by figure 6-12.

b. In the instructions:

manifold

assembly

buildup

(1) Replace subparagraph (12) with new subparagraph - - (12):

(12) Install one of the ~ackiners(11)in the g-roove nearest to the shoulder bf the d v e body (1); behind the packing, install ring (12). (2) Replace subparagraph (14) with new subparagraph (14): (14) Install the third packing (11) in the outer groove of the valve body (1); in front of the packing, install ring (12).

(25) Install unions (25) in manifold assembly (13) and tighten. (4) In subparagraph (361, washer (42) is not used. (5) Replace subparagraphs (37) through (40) with new subparagraphs (37) and (38): (37) Install two gaskets (45) on two unions (46) and lubricate with petrolatum, Federal Specification W-P-236. (38) Install unions (46) in valve assembly (36) and tighten. c. The cylinder and tubing assembly, part No. 396175-25, is built up in the same way as for part No. 396175-23 with the exception that the index numbers of figure 5-3 are changed as follows: 2. KSU17-1 BALL 7. MS21924-6 UNION 13. MS21902-6 UNION 15. MS21908-6 ELBOW 19. MS21902-6 UNION 21. MS21908-6 ELBOW (2 REQD) 23. 370740-345 TUBE ASSEMBLY 24. 370740-347 TUBE ASSEMBLY

T.O. 4S2-23-3

DIFFERENCE DATA SHEEi

37. 38. 39. 40. 41. 42. 43. 44. 45. 46. 47. 48. 49.

373531-3 VALVE ASSEMBLY (PART OF 27) AN 173-6 BOLT 2752-048 NUT LS4893-4 RETAINER AN4H14A BOLT MS20219-4 PULLEY AN960- 10 WASHER AN310-3 NUT MS24665- 134 COTTER PIN AN6290-6 GASKET (4 REQD) MS21902-6 UNION (4 REQD) 149-52825-0090- 180 HOSE ASSEMBLY NOT USED

50. 51 52. 53. 5455.

NOT USED

. 149-52825-0090- 180 HOSE ASSEMBLY

56. 57. 58. 5960.

NOT USED NOT USED 370740-46 TUBE ASSEMBLY (2 REQD) AN6289-6 NUT (2 REQD, SAME AS 18, 29, FIGURE 6-12) MS21908-6 ELBOW (2 REQD, SAME AS 21, 32, FIGURE 6-12) 370740-47 TUBE ASSEMBLY (2 REQD) MS21908-6 ELBOW (SAME AS 57, FIGURE 6-12) MS21908-6 ELBOW (SAME AS 50, FIGURE 6-12) AN6289-6 NUT (2 REQD SAME AS 47, 54FIGURE

Figure 6-11. Nose Landing Gear Assembly, Part No. 396175-17 (Sheet 1 of 2)

T.O. 4S2-233

DIFFERENCE DATA S H E n

88. 89. 90. 91 92. 93. 94.

.

95.

96. 97. 98. 39. 103. 101. 102. 103. 104. 105. 106. 107. 108. 109. 110. 11 1 112. 113. 114. 115. 116.

.

117. 118. 119. 120. 121. 122.

JACK PLUG (PART OF 1) NAS75-18-004 BUSHING 356718-1 ARM 356028-1 BOLT 35.5205-1 TORQUE ARM 356718-2 ARM AN960-1416 WASHER AN320-14 NUT MS20008-91 BOLT MS20002C8 WASHER AN960-816 WASHER EBO8O NUT .MS24665-359 COTTER PIN 15187-1 VIBRATION INSULATOR (2 REQD) 355269-1 LINK NAS1104-30D BOLT AN310-4 NUT 355270-1 BOLT AN960-1016 WASHER (3 REQD) NAS43HTIO-18 SPACER (2 REQD) AN963-816 WASHER AN320-8 NUT MS24665-298 COTTER PIN NAS 1104-30D BOLT AN310-4 NUT M524665-298 COTTER PIN (2 REQD) 357918-1 FITTING 357771-1 CROSSBAR AN6-12 BOLT AN310-6 NUT M524665-134 COTTER PIN 353665 SHIM (2 REQD) NAS1104-19 BOLT (4 REQD) NOT USED AN310-4 NUT (4 REQD)

F

i 6-11. Nose Landing Gear Assembly, Part No.396175-17 (Sheet2 of 2)

T.O. 4S2-23-3

DIFFERENCE DATA SHEET

n

BUILD UP OF MANIFOLD ASSEMBLY ON 372684-1

Figure 6-12. Manifold Assemblies for Part No. 396175-17 (Sheet 1 of 3)

DIFFERENCE DATA SHEET

BUILD UP OF MANIFOLD ASSEMBLY ON 372683- 1

Figure 6-12. Manifold Assemblies for Part No. 396175-17 (Sheet 2 of 3)

T.O. 4S2-23-3

DIFFERENCE DATA SHEET

1 . 372690-1 VALVE BODY (2 REQD) 2. 356356-1 VALVE (2 REQD) 3. 3 3 7 4 5 2 SPRING (2 REQD) 4. 3 5 1 5 1 4 RETAINER ( 2 REQO) 5. AN6290-8 GASKET (2 REQD) 6. AN8144DL PLUG (2 REQD) 7. MS28775-008 PACKING (2 REQD) 8. 3 5 1 5 0 2 PLUG (2 REQD) 9. 52-022-094-0875 PIN (2 REQD) lo. 3 5 1 5 0 3 RlNG ( 2 REQD) l l . MS28775222 PACKING ( 6 REQD) 12. LS4565-27 RlNG (8 REQD) 13. 372684-1 MANIFOLD ASSEMBLY 14. 3 5 1 5 0 6 WASHER 15. NAS670-175 RlNG 16. A N 6 2 9 0 3 GASKET (2 REQD) 17. AN814-3 PLUG ( 2 REQD) 18. AN62896 NUT 19. LS4764-6 RlNG

20. 21. 22. 23. 24. 25. 26. 27. 28. 29. 30. 31. 32. 33. 34. 35.

AN62906 GASKET MS21908-6 ELBOW A N 6 2 9 0 6 GASKET MS21902-6 UNlON AN6290-4 GASKET ( 2 REQD) M S 2 1 9 0 2 4 UNlON ( 2 REQD) 372683-1 MANIFOLD ASSEMBLY 351506 WASHER NAS670-175 RlNG AN62894 NUT LS4764-6 RlNG AN6290-6 GASKET MS21908-6 ELBOW AN6290-6 GASKET MS21902-6 UNlON MS28775-113 PACKING (2 REQD) 36. 373531-1 OR 373531-3 VALVE ASSEMBLY 37. M S 2 0 0 0 5 4 4 BOLT ( 2 REQD)

38. 39. 40. 41. 42. 43. 44. 45. 46. 47. 48. 49. 50. 51. 52. 53. 54. 55. 56. 57.

MS20002C5 WASHER (2 REQD) AN960-516 WASHER (2 REQD) EB054 NUT (2 REQD) M S 2 0 0 0 5 2 8 BOLT NOT USED AN960-516 WASHER EB054 NUT A N 6 2 9 0 4 G A S K O (2 REQD) MS21924-4 UNlON (2 REQD) AN6289-6 NUT LS4764-6 RlNG AN6290-6 GASKET MS21908-6 ELBOW AN6290-6 GASKET MS21902-6 UNlON A N 6 2 8 0 4 VALVE AN6289-6 NUT LS4764-6 RlNG A N 6 2 9 0 4 GASKET MS21908-6 ELBOW

Figure 6-12. Manifold Assemblies for Part No. 396175-17 (Sheet 3 of 3)

6-71/(6-72 blank)

T.O. 4S2-233

DIFFERENCE DATA SHEET

NOSE LANDING GEAR ASSEMBLY (USING STRUT ASSEMBLY, PART NO. 7926829-10)

PART NO. 30010113

THE INSTRUCTIONS CONTAINED IN PRECEDING SECTIONS OF THlS TECHNICAL MANUAL APPLY EXCEPT FOR THE DIFFERENCES LISTED IN THIS DATA SHEET

BUILDUP INSTRUCTIONS. Same as for part No. 396175-13, except as follows: a. In figure 5-1: Sheet 1 is replaced by figure 6-13, sheet 1. Sheet 2, index numbers are changed as follows: 27. MANlFOLD ASSEMBLY (BUILT UP ON 372683-1, SEE FIGURE 6-14). 31. NOT USED 32. NOT USED 33. MANIFOLD ASSEMBLY (BUILT UP ON 372684-1, SEE FIGURE 6-14). Sheet 3 is replaced by figure 6-13, sheet 2. Sheet 4, index No. 61 is changed to be 380239-1 ARM ASSEMBLY. Sheet 5, index numbers are changed as follows: 76. 396175-23 (MODIFIED) CYLINDER AND TUBING ASSEMBLY 82. 345726-8 BRACE ASSEMBLY 83. 345726-7 BRACE ASSEMBLY 84. MAS75-20-005 BUSHING (2 REQD) 85. LH7644-164 NUT (2 REQD) Sheet 6 is replaced by figure 6-13, sheet 3. Sheet 7 is replaced by figure 6-13, sheet 4. Sheet 9 is replaced by figure 6-13, sheet 5.

In instructions: (1) After subparagraph (18), insert new subparagraph (18A): (18A) Install pin (12) in each of the upper trunnions of the steering cylinders. The pins are to be centered in the trunnions to within 0.03 inch. b.

(2) Omit subparagraphs (26) and (27). (3) Replace subparagraphs (38) through (42) with new subparagraphs (38) through (42): (38) Install four gaskets (46) on four unions (47) and lubricate with petrolatum, Federal Specification W-P-236. (39) Install two of the unions (47) in each of the steering cylinders (11). (40) Lubricate the threads of the four unions on the inboard sides of manifold assemblies (27) and (33). (41) Install tube assembly (48) and tighten fittings. (42) Install tube assembly (51) and tighten fittings. (4) Replace subparagraphs (54) through (69) with new subparagraphs (54) through (61): (54) Attach pads (89) and (88A) to the tang (88) by installing insert (89B) into tang. Install two bolts (901, two washers (91), and two nuts (92). Install bolt (89A) into insert. Install bolt (90A) and nut (SOB). Tighten all nuts. (55) Attach support blocks (93 and 94) to the tang (88) using four bolts (951, four washers (961, and four nuts (97) for each of the support blocks. Tighten the nuts. (56) Install tang assembly (98) and two caps (98A and 98B); hold in position with two bolts (99) in the rear holes, four washers (100) (two under the bolt heads and two under the nuts), and two nuts (101). In the forward holes, install two bolts (1021, four washers (100) (two under the bolt heads and two under the nuts), and two nuts (101). Tighten the nuts (101). (57) Install torque arm (104) and hold in position with bolt (1031, washer (1051, and nut (106). Tighten the nut (106) only enough to provide a drag on the torque arm (104) so that it requires from 1 to 15 foot-pounds to move the torque arm (104). Install cotter pin (106A).

DIFFERENCE DATA SHEET

(58) Attach fitting (107) to torque arm (104) using two bolts (108),two spacers (109) between the fitting and the torque arm, two washers (109A1, the nuts. and two nuts (110). Tighten (59) Install two bushings (112) in lever (111). (60) Attach lever assembly (113) to fitting (107); fasten with bolt (114), washer (1151, and nut (116). Tighten the nut but allowing lever assembly (113) to move fjreely, install cotter pin (117). (61) Attach lever (118) to lever assembly (113). Fasten with bolt (1191, washer (1201, and nut (121). Tighten the nut but allowing free relative motion of the two levers, install cotter pin (122). (5) Immediately following subparagraph (721, insert subparagraphs (72A) through (72F): (72A) Install bushings (128B) in bracket (128A). Attach cable (128C) and pin (128D). (72B) Attach bracket assembly (128E) to arm (61) using two bolts (128D, two washers (128G), and nuts (128H). Tighten the nuts. (72C) Attach lever (118) to bracket assembly (128E) using pin (128D). (72D) Loosely install switch (1281) with a nut on the switch side and a nut and washer on the other side of the bracket assembly (128E). Position the tab on the washer in the locating hole in the bracket. (72E) Verify that the strut is fully extended. Adjust switch (1281) so that the switch plunger is just touching lever (118). Secure the switch in position by tightening both nuts. Loosen the nut closest to the switch body until a gap of 0.220 (+0.010) inch is obtained between the nut and the bracket assembly (l28E). Maintain the position of this nut and tighten the other nut. ~afe&vireboth nuts with lockwire, part No. MS20995C32. (72F) Remove pin (128D) to release lever (118); then reinsert pin (128D). (6) Replace subparagraph (95) with new subparagraph (95): (95) Install two seals (1621, two retainer assemblies (1631, and two caps (164) on the axles.

Tighten each cap (164) to 100 foot-pounds while manually rotating wheel. Back off to zero but with all parts still seated. Retighten 50 foot-pounds while manuallv rotating wheel. If not at a locking position, tight& to nearest position. Install lock: screw (165) in each cap (164). SUBASSEMBLY BUILDUP. Same as for part No. 396175-13, except as follows: a.

Figure 5-2 is replaced by figure 6-14.

b. In the instructions:

manifold

assembly

buildup

(1) Replace subparagraph (12) with new subparagraph (12):

(12) Install one of the packings (11)in the groove nearest to the shoulder of the valve body (1); behind the packing, install ring (12). (2) Replace subparagraph (14) with new subparagraph (14): (14) Install the third packing (11) in the outer groove of the valve body (1); in fmnt of the packing, install ring (12). (3) Replace subparagraphs (24) through (27) with new subparagraphs (24) and (25): (24) Install two gaskets (24) on two unions (25) and lubricate with petrolatum, Federal Specification W-P -236. (25) Install unions (25) in manifold assembly (13) and tighten. (4) Replace subparagraphs (27) through (40) with new subparagraphs (37) and (38). (37) Install two gaskets (45) on two unions (46) and lubricate with petrolatum, Federal Specification W-P-236. (38) Install unions (46) in valve assembly (36) . . and tighten. c. The cylinder and tubing assembly, part No. 396175-23 (modified), is built up in the same way as for part No. 396175-23 with the exception that one of the index numbers of figure 5-3 is changed as follows: w

~-

~

12. 697260-1 VALVE

T.O. 4S2-233

DIFFERENCE DATA SHEET

1. 2. 3. 4. 5. 6.

7. 8. 9.

lo. 11. 12. 13. 14.

3401095-1 1 STRUT ASSEMBLY 338948 SPACER DP39B BEARING (2 REQD) MS21025-28 NUT (2 REQD) 355844-1 RETAINER (2 REQD) KWBISSSG BEARING (2 REQD) STEERING COLLAR (PART OF 1) NUT (PART OF 1) BRACKET ASSEMBLY (PART OF 1) 356019-1 SPACER (4 REQD) 402306-3 STEERING CYLINDER (2 REQD) NAS561P-14-16 PIN (2 REQD) 356176-1 SHIELD (2 ,REQD) MS16624-1050 RING (2 REQD)

14

-

&

TYPICAL BOTH STEERING CYLINDERS

Figure 6-13. Nose Landing Gear Assembly, Part No. 3001011-3 (Sheet 1 of 5)

T.O. 4S2-23-3

DIFFERENCE DATA SHEET

DIFFERENCE DATA SHEET

37. 37S531-5 VALVE ASSEMBLY (PART OF 27) 38. AN173-6 BOLT 39. 2752448 NUT 40. LS48994 RETAINER 41. AN4H14A BOLT 42. MS20219-4 PUUm 43. ANge0.10 WASHER 44. AN310-3NUT 45. M524666134 COTER PIN 46. STSPK300-06 GASKET (4 REQD) 47. MSn092-6UNION (4 REQD) 48. 370740-241 TUBE ASSEMBLY 49. NOTUSED

50. NOTUSED 51. 370740.239 TUBE ASSEMBLY

52. 53. 54. 55.

NOTUSED NOTUSED 37074046 TUBE ASSEMBLY (2REQD) AN628W NUT (2 REQD, SAME AS 18.29, FIGURE 614) 58. AN833-6 ELBOW (2 REQD, SAME AS 21,32, FIGURE 614) 57. 37074047TUBE ASSEMBLY (2 RMD) 58. AN833-6 ELBOW (SAME AS 57, FIGURE614) 59. AN8334 ELBOW [SAMEAS SO, FIGURE614) 60. ANazese NUT (2 REQD. SAME AS 47.54 FIGURE 614)

Figure 6-13. Nose Landing Gear Assembly, Part No. 3001011-3 (Sheet 2 of 5)

6 7 6 Change 3

G9100772

T.O. 4S2-233

DIFFERENCE DATA SHEm

3400122-9 TANG 3S15442-1 PLATE 3400122-11 PAD AN57 BOLT 3591SCNY0469INSERT NAS517-3-36 SCREW (2 REQD) NAS1205-38 BOLT MS210426 NUT AN960-10 WASHER (2 REQD) NAss;rsAnnr NUT (3 REQD) 34001226 SUPPORT BLOCK 34001228 SUPPORT BLOCK NAs1108500 BOLT (8 REQD) AN960416 WASHER (8 REQD) A N NUT (8 REQD) 34001223 TANG ASSEMBLY (MADE UP OF 87-88) 3400122-7 CAP 34001228 CAP ANBOLT (2 REQD) ANS60-616 WASHER (8 REQD) NAS679A6 NUT (4 REQD) AN6-57 BOLT (2 REQD) 3400122-13 BOLT 380240-1 TORQUE ARM AN960-1416 WASHER AN320-14 NUT MS24665-359 COlTER PIN 380243-1 FllllNG

NASl103-17 BOLT (2 REQD) NAS42DD6-22 SPACER (2 REQD) AN-1 0 WASHER (2 REOD) MS2l042-3 NUT (2 REQD) 380242-3 LEVER LS3859F3-8 BUSHINO (2 REQD) 380242-1 LEVER ASSEMBLY (MADE UP OF 111 AND 112 AN23-14 BOLT AN980-10 WASHER AN320-3 NUT MS24665-151 COTlER PIN 380244-1 LEVER AN23-14 BOLT ANgBO-10WASHER AN320-3 NUT MS24685-151 COlTER PIN

Figure 6-13. Nose Landing Gear Assembly, Part No. 3001011-3 (Sheet 3 of 5)

T.O. 4S2-233

DIFFERENCE DATA SHEET 1 (REF)

129 (LONGER END)

\

122. 123. 124. 125. 126. 127128. 128A. 128 8. 128 C. 128 D. 128 E

344069CAP 355327-1 HANDLE ASSEMBLY NAS1104-180 BOLT AN310-4 NUT 355326-1 BOLT hAS24665-134 COTTER PIN 380245-3 BRACKET LS3859F4-8 BUSHING 380245-5 CABLE NAS1354S7512D PIN 380245-1 BRACKET ASSEMBLY (MADE UP OF 127A-1270) 128 F NAS1103- 13 BOLT (2 REQD) 128G. ANWO-10 WASHER (2 REQD) 128H. MS21042-3 NUT (2 REQD) 128 I.MS24331-1 SWITCH 129. 339271 CABLE ASSEMBLY 130. MS24M5-132 COTTER PIN (2 REQD) 131 NAS42HT-6-32 SPACER 132. AN520-10RlB SCREW 133 AN%0-10L WASHER 134. NAS679A2 NUT 1%. 33988 BRACKET 136. NOT USED 137. MS27039-1-21 SCREW (2 REQD) 138. NOT USED 139. AN960D10 WASHER (2 REQD) 140. rMS21042-3 NUT (2 REQD)

--

.

130

'

Y

TOP V

p

. .

G9i

Figure 6-13. Nose Landing Gear Assembly, Part No. 3001011-3 (Sheet 4 of 5)

T.O. 4S2-233

DIFFERENCE DATA S H E n

I 164

162. 163. 164. 185.

lee.

167. 168.

161

337119 COLLAR (2 REQD) 3392429 WHEEL AND TIRE ASSEMBLY (2 REQD) 5866Ll2 SE4L (2 REQD) 403311-13 RETAlNER ASSEMBLY (2 REQD) 403311-6 CAP (2 REQD) 403311-7 LOCKSCREW (2 REQD) NOT USED AN8156 UNION (PART OF 76) AN8338 ELBOW (2 REQD, PART OF 76)

Figure 6-13. Nose Landing Gear Assembly,Part No.3001011-3 (sheet 5 of 5)

168

T.O. 4S2-23-3

DIFFERENCE DATA SHEET

BUILD UP OF MANIFOLD ASSEMBLY ON,372684-1

Figure 6-14. Manifold Assemblies for Part No.3001011-3 (Sheet 1 of 3)

DIFFERENCE DATA SHEET

BUILD UP OF MANIFOLD ASSEMBLY O N 372683-1

Figure 6-14. Manifold Assemblies for P a ~No. t 3001011-3 (Sheet 2 of 3)

T.O. 4S2-23-3

1. 2. 3. 4. 5. 6. 7.

8. 9. 10. ll. 12. 13. 14. 15. 16. 17. 18.

372690-4 VALVE BODY (2 REQD) 356356-1 VALVE (2 REQD) 337452 SPRING ( 2 REQD) 351514 RETAINER ( 2 REQD) STSPK300-08 GASKET ( 2 REQD) AN814-8DL PLUG ( 2 REQD) MS2877SO08 PACKING ( 2 REQD) 351502 PLUG ( 2 REQD) NAS561P3-16 PIN ( 2 REQD) 351503 RING (2 REQD) MS28775222 PACKING ( 6 REQD) LS4565-27 RING ( 8 REQD) 372684-1 MANIFOLD ASSEMBLY 351506 WASHER MS16624-1175 RlNG STSPK300-03 GASKET ( 2 REQD) AN8144 PLUG (2 REQD) AN62896 NUT

MS9058-06 RlNG STSPK30M)G GASKET MS21908-6 ELBOW STSPK300-06 GASKET MS2l902-6 UNION STSPK300-04 GASKET ( 2 REQD) M S 2 1 9 0 2 4 UNION ( 2 REQD) 372683-1 MANIFOLD ASSEMBLY 351506 WASHER MS16624-1175 RlNG AN6289-6 NUT MS9058-06 RING STSPK300-06 GASKET MS21908-6 ELBOW STSPK300-06 GASKET MS21902-6 UNlON MS28775-113 PACKING (2 REQD) 36. 373531-5 VALVE ASSEMBLY 37. M S 2 0 0 0 5 3 4 BOLT ( 2 REQD)

19. 20. 21. 22. 23. 24. 25. 26. 27. 28. 29. 30. 31. 32. 33. 34. 35.

38. 39. 40. 41. 42. 43. 44. 45. 46. 47. 48. 49. 50. 5l. 52. 53. 54. 55. 56. 57.

MS20002C5 WASHER (2 REQD) AN96e516 WASHER (4 REQD) STSCD007-10 NUT ( 2 REQD) M S 2 0 0 0 5 2 8 BOLT MS2OOO2C5 WASHER AN960-516 WASHER (2 REQD) STSCD007-10 NUT STSPK30004 GASKET (2 REQD) MS21924-4 UNION ( 2 REQD) AN6289-6 NUT MS9058-06 RING STSPK300-06 GASKET AN833-6 ELBOW STSPK300-06 GASKET (2 REQD) AN815-6 UNION AN6280-6 VALVE AN6289-6 NUT M S 9 0 5 8 4 6 RING STSPK30006 GASKET AN833-6 ELBOW

Figure 6-14. Manifold Assemblies for Part No. 3001011-3 (Sheet 3 of 3)

T.O. 452-23-3

DIFFERENCE DATA SHEET

PART NO. 388067-7 AND 388067-9

NOSE LANDING GEAR ASSEMBLY (USING STRUT ASSEMBLY, PART NOS. 388071-3 AND 792648660)

THE INSTRUCTIONS CONTAINED IN PRECEDING SECTIONS OF THlS TECHNICAL MANUAL APPLY EXCEPT FOR THE DIFFERENCES LISTED IN THlS DATA SHEET

BUILDUP INSTRUCTIONS. Same as for part No. 396175-13, except as follows:

Sheet 8, index numbers are changed a s follows: 157. NAS1104-330 BOLT

Sheet 1is replaced by figure 6-15, sheet 1. Sheet 2, index numbers are changed as follows: 21. MS21042-4 NUT 23. MS20392-3C-49 PIN 27. MANIFOLD ASSEMBLY (BUILT UP ON 372683-1, SEE FIGURE 6-16). 31. NOT USED. 32. NOT USED. 33. MANIFOLD ASSEMBLY (BUILT UP ON 372684-1, SEE FIGURE 6-16). Sheet 3 is replaced by figure 6-15, sheet 2. Sheet 4, index numbers are changed as follows: 61. 388069-1 ARM ASSEMBLY 63. AN960-1416L WASHER Sheet 5, index numbers are changed as follows: 76. 396106-1 or 396106-3 CYLINDER AND TUBING ASSEMBLY 77. 371670-1 BOLT 78. 372667-1 WASHER 82. 371689-7 BRACE ASSEMBLY 83. 371689-8 BRACE ASSEMBLY 84. 756001-1 SPACER (2 REQD) 85. LH7644-164 NUT (2 REQD) Sheet 6 is replaced by figure 6-15, sheet 3. Sheet 7 is replaced by figure 6-15, sheet 4.

158. AN320-4 NUT Sheet 9, index numbers are changed a s follows: 161. 33924204 or 339242-9 WHEEL AND TIRE ASSEMBLY (2 REQD ON 388067-7) 339242-7 or 339242-13 WHEEL AND TIRE ASSEMBLY (2 REQD ON 388067-9) 167. MS21902-6 UNION (PART OF 76) 168. MS21908-6 ELBOW (2 REQD, PART OF 76) b.

In instructions:

(1) In subparagraph (171, change torque value to 210 (+lo) foot-pounds.

(2) After subparagraph (181, insert new subparagraph (18A): (18A) Install pin (12) in each of the upper trunnions of the steering cylinders. The pins are to be centered in the trunnions to within 0.03 inch. (3) Omit subparagraphs (26) and (27). (4) Replace subparagraphs (38) through (42) with new subparagraphs (38) through (42): (38) Install four gaskets (46) on four unions (47) and lubricate with petrolatum, Federal Specification W-P-236. (39) Install two of the unions (47) in each of the steering cylinders (11). (40) Lubricate the threads of the four unions on the inboard sides of manifold assemblies (27) and (33). (41) Install tube assembly (48) and tighten fittings.

T.O. 4S2-233

DIFFERENCE DATA SHEET

(42) Install tube assembly (51) and tighten fittings. (5) Replace subparagraph (51) with new subparagraph (51): (51) Attach brace assemblies (82 and 83) to the strut assembly (1). Install spacer (84) and nut (85) on end of pin having the longer threads; tighten this nut against the shoulder of the pin. Install racer (84) and nut (85) on the other end of the pin; tighten this nut against the nut on the opposite end of the pin. (6) Replace the note preceding subparagraph (58) with the following note and subparagraph (57A): NOTE

Perform subparagraphs (57A) through (60A) only if a new arm (90) and/or arm (93) is being installed. (57A) Remove screws holding jack plug (88) to the bottom of strut assembly (1)and remove jack plug. (7) Add subparagraph (60A) immediately following subparagraph (60): (60A) Replace jack plug (88) and screws removed in subparagraph (57A). Tighten the screws and safetywire using lockwire, part No. MS20995C32. (8) Replace subparagraph (69) with new subparagraphs (69) and (69A). (69) Install crossbar (115) and shims (119) in arms (90 and 93) . Peel laminations of shim to fit. The maximum allowable gap is 0.005 inch. When the shim thickness has been determined, paint the shims with zinc chromate primer, Federal Specification TI'-P-1757. (69A) Secure the crossbar (115) and shims (119) in position with four bolts (120) and nuts (122). Tighten the nuts. (9) Replace subparagraph (78) with new subparagraph (78). (78) Route the other end of the cable around the collar pulley. Locate bracket (135) in position and determine the thickness of laminated shim (136) required to obtain a minimum clearance of 0.010 to 0.020 inch between the outer edge of the dollar (7) and the bracket (135). Install the bracket (135) and shim (136); wet using corrosion-preventative sealant per Specification MIES-8802B2 on the faying surfaces. Secure in place with two

screws (137), two washers (1381, two washers (1391, and two nuts (140). Before tightening the nuts, position the bracket to provide the minimum vertical clearance obtainable (but not less than 0.020 inch) between the top of the collar (7) and the adjacent lower surface of the bracket (135). SUBASSEMBLY BUILDUP. Same as for part No. 396175-13, except as follows: a. Figure 5-2 is replaced by figure 6-16. b. In the instructions:

manifold

assembly

buildup

(1) Replace subparagraph (12) with new subparagraph (12):

(12) Install one of the packings (11)in the groove nearest to the shoulder of the body (1); behind the packing, install ring (12). (2) Replace subparagraph (14) with new subparagraph ( 14): (14) Install the third packing (11) in the outer groove of the valve body (1); in front of the packing, install ring (12). (3) Replace subparagraphs (24) through (27) with new subparagraphs (24) and (25): (24) Install two gaskets (24) on two unions (25) and Iubricate with petrolatum, Federal Specification W-P-236. (25) Install unions (25) in manifold assembly (13) and tighten. (4) Replace subparagraphs (27) through (40) with new subparagraphs (37) and (38): (37) Install two gaskets (45) on two unions (46) and lubricate with petrolatum, Federal Specification W-P-236. (38) Install unions (46) in valve assembly (36) and tighten. c. The cylinder and tubing assembly, part No. 396106-1, is built up in the same way as for part No. 396175-23 with the exception that the index numbers of figure 5-3 are changed as follows: 2. KSU17-1 BALL 7. MS21924-6 UNION 12. 697260-1 VALVE 13. MS21902-6 UNION 15. MS21908-6 ELBOW 19. MS21902-6 UNION

T.O. 4S2-233

DIFFERENCE DATA SHEET

21. MS219-8-6 ELBOW (2 REQD) 23. 370740-345 TUBE ASSEMBLY 24. 370740-347 TUBE ASSEMBLY d. The cylinder and tubing assembly, part No. 396106-3, is built up in the same way as for part No. 396175-23 with the exception that the index numbers of figure 5-3 are changed as follows: 1. 3400770-5 CYLINDER ASSEMBLY

12. 697260-1 VALVE 13. MS21902-6 UNION 14. LS4634-6 GASKET 15. MS21908-6 ELBOW 18. LS4634-6 GASKET 19. MS21902-6 UNION 20. 154634-6 GASKET

2. KSU17-1 BALL 7. MS21924-6 UNION

21. MS21908-6 ELBOW (2 REQD)

8. LS4634-6 GASKET

23. 370740-345 TUBE ASSEMBLY

11. LS4634-6 GASKET

24. 370740-347 TUBE ASSEMBLY

T.O. 482-2343

DIFFERENCE DATA SHEW

1. 2. 3. 4.

5. 6. 7. 8. 9.

lo. 11. 12. 13. 14.

388071-3 STRUT ASSEMBLY 338948 SPACER Y T A I W BEARING (2 REQD) MS21025-28 NUT (2 REQD) 355844-1 RETAINER (2 REQD) KWB15SSG BEARING (4 REQD) STEERING COLLAR (PART OF 1) NUT (PART OF 1) BRACKET ASSEMBLY (PART OF 1) 356019-1 SVACER (4 REQD) 695568-1 STEERING CYLINDER (2 REQD) NAS561P-14-16 PIN (2 REQD) 356176-1 SHIELD (2 REQD) MS16624-1050 RING (2 REQD)

14

4 4

TYPICAL BOTH STEERING CYLINDERS

Figure 615. Nose Lunding Gear Assembly, Part Nos. 388067-7and 388067-9(Sheet 1 of 4)

T.O. 4S2-233

DIFFERENCE DATA SHEET

37. 38. 39. 40. 41. 42. 43. 44. 45. 46. 47. 48. 49.

373531-5 VALVE ASSEMBLY (PAPT OF 26) AN 173-6 BOLT 2752-048 NUT LS4893-4 RETAINER AN4H14A BOLT MS20219-4 PULLEY AN960-10 WASHER AN310-3 NUT MS24665-134 COTTER PIN LS4634-6 GASKET (4 REQD) MS21902-6 UNION (4 REQD) 370740-241 TUBE ASSEMBLY NOT USED

50. 51. 52. 53. 54.

55. 56. 57. 58. 59. 60-

NOT USED 370740-239 TUBE ASSEMBLY NOT USED NOT USED 370746-46 TUBE ASSEMBLY (2 REQD) AN6289-6 NUT (2 REQD, SAME AS 18, 29 FIGLJRE6-16) MS2 1908-6 ELBOW (2 REQD , SAME AS 2 1, 32, FIGURE 6-16) 370740-47 TUBE ASSEMBLY (2 REQD) MS21908-6 ELBOW (SAME AS 57, FlGURE6-16) MS21908-6 ELBOW (SAME AS 50, FIGURE6-16) AN6289-6 NUT (2 REQD, SAME AS 47, 54, FIGURE 6-16)

Figure 6-15. Nose Landing Gear Assembly, Part Nos. 388067-7 and 3888067-9 (Sheet 2 of 4)

G91007EO

T.O. 4S2-23-3

DIFFERENCE DATA S H E D

88. 89. 90. 91. 92. 93. 94. 95. 96. 97. 98. 99. 100. 101. 102. 103. 104. 105. 1D6. 107. 108. 109. 110. 111. 112. 113. 114. 115. 116. 117. 118. 119. 120. 121. 122.

JACK PLUG (PART OF 1) NAS75-18-004 BUSHING 356718-1 ARM 388119-3 BOLT 388068-1 TORQUE ARM 356718-2 ARM AN960-1416 WASHER AN320-14 NUT MS20008-91 BOLT MS20002C8 WASHER AN960-816 WASHER 57585-820 NW MS24665-359 COTTER PIN J5187-1 VIBRATION INSULATOR (2 REQD) 355269-1 LINK NAS 1104-30D BOLT AN310-4 NUT 355270-1 BOLT AN960-1016 WASHER (3 REQD) NAS43-10-18 SPACER (2 REQD) AN960-816 WASHER AN320-8 NUT MS24665-298 COTTER PIN NAS 1 104-30D BOLT AN310-4 NUT MS24665-298 COTTER PIN (2 REQD) 357918-1 FITTING 357771-1 CROSSBAR AN6-12 BOLT AN310-6 NUT MS24665-134 COTTER PIN 353665 SHIM (2 REQD) NAS1104-19 BOLT (4 REQD) NOT USED h621042-4 NUT (4 REQD)

Figure 615. Nose Landing Gear Assembly, Part Nos. 388067-7 and 3888067-9 (Sheet 3 of 4)

T.O. 492-23-3

DIFFERENCE DATA SHEET

129 (LONGER END)

123. 344069 CAP 124. 355327-1 HANDLE ASSEMBLY 125. NAS1104-18D BOLT 126. AN310-4 NUT 127. 355326-1 BOLT 128. MS24665-1% COTTER PIN 129. 339271 CABLE ASSEMBLY 130. MS24665-132 COTTER PIN (2 REQD) 131. NAS42HT-6-32 SPACER 132. NAS603- 18 SCREW 133. AN960-10L WASHER 134. MS21042-3 NUT 135. 339288 BRACKET 136. LS5940-3 LAMINATED SHIM 137. NAS623-3-14 SCREW (2 REQD) 138. NAS1197-10 WASHER (2 REQD) 139. AN960ClOL WASHER i 2 REQD) 140. MS21042-3 NUT (2 REQD)

TOP VIEW

Figure 6-15. Nose Landing Gear Assembly, Part Nos. 388067-7 and 3888067-9 (Sheet 4 of 4)

T.O. 4S2-23-3

DIFFERENCE DATA S H E n

BUILD UP OF MANIFOLD ASSEMBLY ON 372604-1

Figure 816. Manifold Assemblies for Part Nos. 388067-7and 388067-9(Sheet 1 of3)

T.O. 4S2-233

DIFFERENCE DATA SHEET

BUILD UP OF MANIFOLD ASSEMBLY ON 372683 -1

Figure 6-16. Manifold Assemblies for Part Nos. 388067-7 and 388067-9 (Sheet 2 of 3)

T.O. 4S2-233

DIFFERENCE DATA SHEET

1. 2. 3. 4. 5. 6. 7.

372690-1 VALVE BODY ( 2 REQD) 356356-1 VALVE (2 REQD) 3 3 7 4 5 2 SPRING ( 2 REQD) 3 5 1 5 1 4 RETAINER ( 2 REQD) LS4634-8 GASKET ( 2 REQD) AN8144DL PLUG ( 2 REQD) M S 2 8 7 7 5 0 0 8 PACKING ( 2 REQD) 8. 3 5 1 5 0 2 PLUG ( 2 REQD) 9. NAS561P3-16 PIN ( 2 REQD) 10. 3 5 1 5 0 3 RlNG ( 2 REQD) ll.MS28775-222 PACKING ( 6 REQD) l2. LS4565-27 RlNG ( 8 REQD) 13. 372684-1 MANIFOLD ASSEMBLY 14. 3 5 1 5 0 6 WASHER 15. MS16624-1175 RlNG 16. LS4634-3 GASKET ( 2 REQD) 17. A N 8 1 4 4 PLUG ( 2 REQD) 18. A N 6 2 8 9 4 NUT 19. LS4764-6 RlNG

20. 21. 22. 23. 24. 25. 26. 27. 28. 29. 30. 31. 32. 33. 34. 35.

LS4634-6 GASKET MS21908-6 ELBOW LS4634-6 GASKET MS21902-6 UNlON LS4634-6 GASKET ( 2 REQD) M S 2 1 9 0 2 4 UNlON ( 2 REQD) 372683-1 MANIFOLD ASSEMBLY 3 5 1 5 0 6 WASHER M S l 6 6 2 4 - l l 7 5 RlNG A N 6 2 8 9 4 NUT LS4764-6 RlNG LS4634-6 GASKET MS21908-6 ELBOW LS4634-6 GASKET MS21902-6 UNlON MS28775-113 PACKING (2 REQD) 36. 373531-1 OR 371531-3 VALVE ASSEMBLY 37. MS20005-34 BOLT ( 2 REQD)

38. 39. 40. 41. 42. 43. 44. 45. 46. 47. 48. 49. 50. 51. 52. 53. 54. 55. 56. 57.

MS20002C5 WASHER ( 2 REQD) AN960-516 WASHER ( 2 REQD) 57585-524 NUT ( 2 REQD) MS20005-28 BOLT 3 4 5 5 7 0 WASHER AN960-516 WASHER 5 7 5 8 8 5 2 4 NUT L S 4 6 3 4 4 GASKET ( 2 REQD) MS21924-4 UNlON ( 2 REQD) AN6289-6 NUT LS4764-6 RlNG LS4634-6 GASKET MS21908-6 ELBOW LS4634-6 GASKET MS21902-6 UNlON A N 6 2 8 0 6 VALVE AN6283-6 NUT LS4764-6 RlNG LS4634-6GASKm MS21908-6 ELBOW

Figure 6-16. Manifold Assemblies for Part Nos.388067-7and 388067-9(Sheet 3 of 3)

T.O. 4S2-233

DIFFERENCE DATA SHEET

PART NO. 3 3 0 3 5 9 5 1 AND 3 3 0 3 5 9 5 5

NOSE LANDING GEAR ASSEMBLY (USING STRUT ASSEMBLY, PART NOS. 3303591-1,3303591-3, AND 7926487-10)

THE INSTRUCTIONS CONTAINED IN PRECEDING SECTIONS OF THIS TECHNICAL MANUAL APPLY EXCEPT FOR THE DIFFERENCES LISTED IN THIS DATA SHEET

161. 339242-13 WHEEL AND TIRE ASSEMBLY (2 REQD) 167. MS21902-6 UNION (PART OF 76)

BUILDUP INSTRUCTIONS. Same as for part No. 39'6175-13, except as follows: a. Infigure5-1: Sheet 1is replaced by figure 6-17, sheet 1. Sheet 2 is replaced by figure 6-17, sheet 2. Sheet 3 is replaced by f i e 6-17, sheet 3. Sheet 4 is replaced by figure 6-17, sheet 4. Sheet 5, index numbers are changed as follows: , 76. 396106-3 CYLINDER AND TUBING ASSEMBLY USED ON STRUT, PART NO. 3303595-1; AND 396106-5 OR 396106-7 USED ON STRUT, PART NO. 3303595-5. 77. 371870-1 BOLT 78. 372667-1 WASHER 82. 371689-7 BRACE ASSEMBLY USED ON STRUT, PART NO. 3303595-1; AND 371689-11 USED ON STRUT, PART NO. 3303595-5. 83. 371689-8 BRACE ASSEMBLY USED ON STRUT, PART NO. 3303595-1; AND 371689-12 USED ON STRUT, PART NO. 3303595-5. 84. 756001-1 SPACER (2 REQD) 85. LH7644-164 NUT (2 REQD) 86. 345731 SPACER USED ON STRUT, PART NO. 3303595-1; AND 345731-3 USED ON STRUT, PART NO. 3303595-5. Sheet 6 is replaced by figure 6-17, sheet 5. Sheet 7 is replaced by figure 6-17, sheet 6. Sheet 8 is replaced by figure 6-17, sheet 7. Sheet 9, index numbers are changed as follows:

168. MS21908-6 ELBOW (2 REQD, PART OF 76) b.

In instructions:

(1) In subparagraph (171, change torque value to 210 (+lo) foot-pounds. (2) After subparagraph (181, insert new subparagraph (18A). (18A) Install pin (12) in each of the upper trunnions of the steering cylinders. The pins are to be centered in the trunnions to within 0.03 inch. (3) After subparagraph (221, insert new subparagraphs (22A) and (22B): (22A) Loosen the nut (22A) on the inner eyebolt (22B). Position the bracket assembly (22) in place. Lift the inner eyebolt (22B) to enable pin (23) with washer (24) to be inserted. Insert the pin (23). (22B) Retighten nut (22A) making sure that the eyebolt (22B) is correctly aligned and that the bracket assembly (22) is free to pivot. (4) Replace subparagraph (23) with new subparagraph (23): (23) Install washer (24) and cotter pin (25) on pin (23). (5) Omit subparagraphs (26) and (27). (6) Replace subparagraphs (28) through (42) with new subparagraphs (38) through (42): (38) Install four gaskets (461,on four unions (47) and lubricate with petrolatum, Federal Specification W-P-236. (39) Install two of the unions (47) in each of the steering cylinders (11).

DIFFERENCE DATA SHEET

(40) Lubricate the threads of the two unions and two elbows (50 and 53) on the inboard sides of manifold assemblies (27) and (33). (41) Install tube assembly (48). Tighten nut (49) on elbow (50). Tighten fittings on tube assembly. (42) Install tube assembly (51). Tighten nut (52) on elbow (53). Tighten fittings on tube assembly. (7) Replace subparagraph (49) with new subparagraph (49): (49) Attach bracket (71) to fulcrum of strut (1)using screw (72) in the forward position, screw

(73) in the aft position, two washers (741, and two nuts (75). (8) Replace subparagraph (51) with new subparagraph (51): (51) Attach brace assemblies (82 and 83) to the strut assembly (1). Install spacer (84) and nut (85)on the end of the pin having the longer threads. Tighten this nut against the shoulder of the pin. Install spaces (84) and nut (85) on the other end of the pin. Tighten this nut against the nut on the opposite end of the pin. (9) Replace the note preceding subparagraph (58) with the following note and subparagraph (57A): NOTE

Perform subparagraph (57A) through (60A) only if a new arm (90) andlor arm (93) is being installed. (57A) Remove screws holding jack plug (88) to the bottom of the strut assembly (1). Remove the jack plug. (10) Add subparagraph (60A) immediately following subparagraph (60): (60A) Replace jack plug (88) and screws removed in subparagraph (57A). Tighten the screws and safetywire using lockwire, part No. MS20995C32. (11) Replace subparagraph (69) with new subparagraphs (69) and (69A):

(69) Install crossbar (115) and shims (119)in arms (90 and 93). Peel laminations of shim to fit; the maximum allowable gap is 0.005 inch. When the shim thickness has been determined, paint the shims with zinc chromate primer, Federal Specification 'IT-P-1757.

(69A) Secure the crossbar (115) and shims (119) in position with four bolts (1201, four washers (121), and four nuts (122). Tighten the nuts. (12) Replace subparagraph (78) with new subparagraph (78): (78) Route the other end of the cable around the collar pulley. Locate bracket (135) in position and determine the thickness of laminated shim (135) required to obtain a minimum clearance of 0.010 to 0.020 inch between the outer edge of the collar (7) and the bracket (135). Install the bracket (135) and shims (136) wet using corrosion-preventive sealant per Specification MIL-S-8802B2 on the faying surfaces. Secure in place with two screws (137), two washers (1381, two washers (1391, and two nuts (140). Before tightening the nuts, position the bracket to provide the minimum vertical clearance obtainable (but not less than 0.020 inch) between the top of the collar (7) and the adjacent lower surface of the bracket (135). (13) Replace subparagraph (85) with new subparagraph (85): (85) Loosely install two pulleys (152), two guard pins (1541, four washers (156A), bolt (1571, and nut (158)in the forward end of the bracket (71). Route the cables under the pulleys. Locate the guard pins (154) and tighten the nut (158). Install cotter pin (159). SUBASSEMBLY BUILDUP. Same as for part No. 396175-13, except as follows: a. Figure 5-2 is replaced by figure 6-18. b. In the manifold assembly buildup instructions: (1) Replace subparagraph (12) with new subparagraph (12): (12) Install one of the packings (11)in the groove nearest to the shoulder of the valve body (1); behind the packing, install ring (12). (2) Replace subparagraph (14) with new subparagraph (14): (14) Install the third packing (11) in the outer groove of the valve body (1); in front of the packing, install ring (12).

(3) Replace subparagraphs (24) through (27) with new subparagraphs (24) and (25): (24) Install nut (241, ring (251, and gasket (26) on each of two elbows (27). The nut (24) should be positioned such that the gasket (26) fits into the groove in the elbow (27) and not on the screw

T.O. 4S2-233

DIFFERENCE DATA SHEET

threads. Lubricate with petrolatum, Federal Specification W-P-236. (25) Install elbows (27) in the manifold assembly (13). Tighten the nuts (24) finger tight. (4) Replace subparagraphs (37) through (40) with new subparagraphs (37) and (38): (37) Install two gaskets (47) on two unions (48) and lubricate with petrolatum, Federal Specification W-P-236. (38) Install unions (48) in valve assembly (38) and tighten. c. The cylinder and tubing assembly, part No. 396106-3, is built up in the same way as for part No. 396175-23 with the exception that the index numbers of figure 5-3 are changed as follows: 1.

3400770-5 CYLINDER ASSEMBLY

2.

KSU17-1BALL

7.

MS21924-6 UNION

8.

LS4634-6 GASKET

11.

LS4634-6 GASKET

12. 13.

697260-1 VALVE MS21902-6 UNION

14.

LS4634-6 GASKET

15. 18. 19. 20.

MS21908-6 ELBOW LS4634-6 GASKET MS21902-6 UNION LS4634-6 GASKET

21.

MS21908-6 ELBOW (2 REQD)

23. 24.

370740-345 TUBE ASSEMBLY 370740-347 TUBE ASSEMBLY

T.O. 4S2-23-3

DIFFERENCE DATA SHEET

1. 2. 3. 4. 5. 6.

7. 8.

9.

lo. 11. 12. 13. 14.

15.

3303591-ID, -3 STRUT ASSEMBLY 338948 SPACER YTA106A BEARING (2 REQD) MS21025-28 NUT (2 REQD) 355844-1 RETAINER (2 REQD) KWBlSSSG BEARING (4 REQD) STEERING COLLAR (PART OF 1) NUT (PART OF 1) BRACKET ASSEMBLY (PART OF 1) 356019-1 SPACER (4 REQD) 695568-1 -5 STEERING CYLINDER (2 REQD) NAS561P-14-16 PIN (2 REQD) 356176-1 SHIELD (2 REQD) MS16224-1050 RING (2 REQD) NOT USED

D.

P/PICAL BOTH STEERING CYLINDERS

Figure 6-17. Nose Landing Gear Assembly, Part Nos. 3303595-1 and 3303595-5 (Sheet 1 of 7)

DIFFERENCE DATA SHEET

16. 17. 18. 19. 20. 21. 22. 22A. 22 B. 23. 24. 25. 26.

AN316-4R NUT 35455322 LINKEND 345571 LINK END NAS334CPA12 BOLT AN%O-416 WASHER MS21042-4 NUT BRACKETASSEMBLY 339270 D,-3 MS21042-5 NUT (PART OF 1) AN44-5A EYEBOLT (PART OF 1) MS20392-3C-5 1 PIN AN960-416L WASHER (2 REQD) MS24665-151 COTTER PIN 351505 SPACER (2 REQD)

27. MANIFOLD ASSEMBLY (BUILT UP O N 372683-1,D. -5 SEE FlGURE6-18) 28. NAS1304-18H BOLT (2 REQD) 29. AN960D416 WASHER (2 REQD) 30. MS21042-4 NUT (2 REQD) 31. N O T USED 32. N O T USED 33. MAN IFOLD ASSEMBLY (BUILT UP O N FIGURE 6-18) 372684-1, D,-~DsEE 34- NAS1304-18H BOLT (2 REQD) 35. AN960D416 WASHER (2 REQD) 36. MS21042-4 NUT (2 REQD)

Figure 6-17. Nose Landing Gear Assembly, Part Nos. 3303595-1 and 3303595-5 (Sheet 2 of 7)

T.O. 4S2-23-3

DIFFERENCE DATA SHEET

37. 38. 39. 40. 41. 42. 43.

373531-5 VALVE ASSEMBLY (PART OF 27) NAS1303-6D BOLT 2752-048 NUT L54893-4 RETAINER NAS1304-15H BOLT MS20219-4 PULLEY AN960-10 WASHER 4.AN310-3 NUT 45. MS24665- 134 COTTER PIN 46. LS4634-6 GASKET (4 REQD) 47. MS21W2-6 U N I O N (4 REQD) 48. 370740-417 TUBE ASSEMBLY 49. AN62B9-4 NUT (SAME AS 24, FIGURE 6-18) 50. MS21907-4 ELBOW (SAME AS 27, FIGURE 6-18)

51. 52. 53. 54. 55. 56. 57. 58. 59. 60.

370740-415 TUBE ASSEMBLY AN6289-4 NUT (SAME AS 24 FIGURE 6-18 ) MS21907-4 ELBOW (SAME AS 27, FlGURE 6-18) 370740-46 TUBE ASSEMBLY (2 REQD) AN6289-6 NUT (2 REQD, SAME AS 10, 31, FIGURE 6-18) MS21908-6 ELBOW (2 REQD SAME AS 21, 34, FIGURE 6-18) 370740-47 TUBE ASSEMBLY (2 REQD) MS21908-6 ELBOW (SAME AS 59, FIGURE 6-18) MS21908-6 EBLOW (SAME AS 52,FIGURE 6-18) AN6289-6 NUT (2 REQD, SAME AS 49, 56, FIGURE 6-18)

,

Figure 6-27. Nose Landing Gear Assembly, Part Nos.3303595-1and 3303595-5(Sheet 3 of 7)

T.O. 452-23-3

DIFFERENCE DATA S H E n

7 6-3

D, 12)

61. 388069-1 -5 ARM ASSEMBLY 62. 356028-1 BOLT 63. AN960-1416L WASHER 64. AN320-14 NUT 65. MS24665-359 COTTER PIN 66. 351516-5 SEAL ASSEMBLY (4 REQD) 67. NAS1108-20D BOLT (2 REQD) 68. AN960-816 WASHER (2 REQD) 69. AN320-8 NUT (2 REQD) 70. MS24665-134 COTTER PIN (2 REQD) 71. 339269 BRACKET 72. NAS517-4-7 SCREW 73. NAS517-4- 14 SCREW 74. AN960D416 WASHER (2 REQD) 75. M521042-4 NUT (2 REQD)

TYPICAL BOW STEERING CYLINDERS (11)

G98C1648

Figure 6-17. Nose Landing Gear Assembly,Part Nos.3303595-1 and 3303595-5 (Sheet 4 of 7)

T.O. 4S2-23-3

DIFFERENCE DATA SHEET

88. 89. %. 91.

JACK PLUG (PART OF 1) NAS75- 18-004 BUSHING 356718-1 -3 ARM 388119-3 1 -5 2 BOLT -5 2 TORQUE ARM -5 ARM AN960- 1416L WASHER AN320-14 NUT MS20008-91 BOLT MS20002C8 WASHER AN960-816 WASHER 51585-820 N UT MS24665-359 COTTER P I N J5187-1 VIBRATION INSULATOR (2 REQD) 355269-111) NASl104-30D BOLT AN310-4 NUT 355270-1 BOLT AN960-1016 WASHER (3 REQD) NAS43HT10-18 SPACER (2 REQD) AN960-816 WASHER AN320-8 NUT MS24665-287 COTTER PIN NAS1104-30D BOLT AN310-4 NUT MS24665-134 COlTER PIN (2 REQD) 357918-1 -5 2 FITTING sm1-1 1 -3 2 CROSSBAR AN6-12 BOLT AN310-6 NUT MS24665-134 COTTER PIN 353665 SHIM (2REQD) NAS1104-20 BOLT (4 REQD) AN960D416 WASHER (4 REQD) MS21042-4 NUT (4 REQD)

iz: %: 94-

95. 96. 97. 98. 99. 100. 101. 102. 103. 104. 105. 106. 107108. 109. 110. 111. 112. 113. 114.

11s. 116. 117. 118. 119. 120. 121. 122.

B: B,

. .118

,-~DL~NK

B B

Figure 6-17. Nose Landing Gear Assembly, Part Nos. 3303595-1 and 3303595-5 (Sheet 5 of 7 )

DIFFERENCE DATA SHER

1 (REF)

TOP VIEW

123. 124. 125. 126. 127. 128. 129. 130. 131.

3 4 4 0 6 9 D . -3 CAP -3 355327-1 HANDLE ASSEMBLY NAS1104-18D BOLT AN310-4 NUT 355326-1 BOLT MS24665-134 COllER PIN 339271 CABLE ASSEMBLY MS24665-182COlTER PIN (2 REQD) NAS42HT-6-32 SPACER

D,

132. 133. 134. 135. 136. 137. 138. 139. 140-

NAS603- 18P SCREW AN960-10L WASHER MS21042-3 NUT 339288 -5 BRACKET 155940-3 LAMINATED SHIM NAS623-3-14 SCREW (2 REQD) NASl187-10 WASHER (2 REQD) AN960-416L WASHER (2 REQD) MS21042-3 NUT (2 REQD)

D,

Figure 6-17. Nose Landing GearAssembly, Part Nos. 3303595-1 and 3303595-5 (Sheet 6 of 7)

T.O. 4S2-23-3

DIFFERENCE DATA SHE=

NOTE. D U S E D ON NLG ASSEMBLY, PART NO. 3303595-1. B U S E D ON NLG ASSEMBLY, PART NO. 3303595-5.

141. 142. 143. 144. 145. 146. 147. 148. 149. 150. 151. 152. 153. 154. 155. 156. 156A. 157. 158. 159.

2752-048 NUT MS20219-4 PULLEY 339272-3 GUARD PIN (2 REQD) AN960D416 WASHER AN960-416L WASHER NAS1304-15H BOLT 339272-3 GUARD PIN (2 REQD) AN960D416 WASHER AN960-416L WASHER 2752-048 NUT (2 REQD) LS4893-4 RETAINER (2 REQD) MS20219-4 PULLEY (4 REQD) AN960D416 WASHER (2 REQD) 339272-3 GUARD PIN (6 REQD) AN960ClOL WASHER (2 REQD) NAS1304-15H BOLT (2 REQD) AN960-416L WASHER (4 REQD) NASllO4-32D BOLT AN320-4 NUT MS24665-134 COTTER PIN

Figure 6-17. Nose Landing Gear Assembly, Part Nos. 3303595-1 and 3303595-5 (Sheet 7 of 7)

DIFFERENCE DATA SHEET

17 ..

BUILD UP OF MANIFOLD ASSEMBLY O N 372684-1

D,-3

Figure 6-18. Manifild Assemblies for Part Nos.3303595-1and 3303595-5(Sheet I of 3)

T.O. 482-233

DIFFERENCE DATA SHEET

BUIU) UP OF MANIFOLD ASSEMBLY ON 372683-1 ll), -5

Figure 6-18. Manifbld Assemblies fir Part Nos. 3303595-1 and 3303595-5 (Sheet 2 of 3)

T.O. 4S2-23-3

DIFFERENCE DATA SHEET 1. 372690-1 D.-3 BVALVE BODY ( 2 REQD) 2. 35635&1 VALVE ( 2 REQD) 3. 337452 SPRING ( 2 REQD) 4. 351514 RETAINER ( 2 REQD) 5. LS4634-8 GASKET ( 2 REQD) 6. AN814-8DL PLUG ( 2 REQD) 7. M S 2 8 7 7 5 0 0 8 PACKING ( 2 REQD) 8. 351502 PLUG ( 2 REQD) 9. NAS561P3-16 PIN ( 2 REQD) lo. 351503 RING D,-3 (2 REQD) ll.MS28775-222 PACKING (6 REQD) l2. LS4565-27 RING ( 8 REQD) 13. 372684-1 MANIFOLD ASSEMBLY 14. 3 5 1 5 0 6 WASHER 15. M S l 6 6 2 4 l l 7 5 RING 16. LS4634-3 GASKET ( 2 REQD) 17. AN814-3DL PLUG ( 2 REQD) 18. AN62894 NUT 19. MS28773-06 RlNG

20. 21. 22. 23. 24. 25. 26. 27. 28. 29. 30. 31. 32. 33. 34. 35. 36. 37.

LS4634-6 GASKET MS21908-6 ELBOW LS4634-6 GASKET MS21902-6 UNION AN62894 NUT (2 REQD) MS28775-04 RING (2 REQD) LS4634-4 GASKET ( 2 REQD) MS219074 ELBOW ( 2 REQD) 372683-1 MANIFOLD ASSEMBLY 351506 WASHER MS16624-3l75 RING AN6289-6 NUT MS28773-06 RING LS4634-6 GASKET MS21908-6 ELBOW LS4634-6 GASKET MS21902-6 UNION MS28775113 PACKING ( 2 REQD) 38. 373531-5 B,-7 BVALVE ASSEMBLY 39. M S 2 0 0 0 W 4 BOLT ( 2 REQD)

40. 41. 42. 43. 44. 45. 46. 47. 48. 49. 50. 51. 52. 53. 54. 55. 56. 57. 58.

MS20002C5 WASHER ( 2 REQD) AN960-516 WASHER ( 2 REQD) 5 7 5 8 5 5 2 4 NUT (2 REQD) M S 2 0 0 0 M 0 BOLT MS20002C5 WASHER AN960-516 WASHER 57585-524 NUT lS4634-4 GASKET ( 2 REQD) MS21924-4 UNION ( 2 REQD) AN6289-6 NUr MS28773-06 RlNG LS4634-6 GASKET M S 2 1 9 0 m ELBOW LS4634-6 GASKET M S U 9 0 2 - 6 UNION AN62806 VALVE AN62894 NUT MS28773-06 RlNG LS4634-6GASKET

59. M S 2 1 9 0 8 6 ELBOW

m D USED ON NLG ASSEMBLY, PART NO. 3303595-1 D USED ON NLG ASSEMBLY, PART NO. 3303595-5 Figure 6-18. Manifold Assemblies for Part Nos.3303595-1 and 3303595-5 (Sheet 3 of 3)

6-105/(6-106 blank)

T.O. 4S2-233

DIFFERENCE DATA SHEET -

NOSE LANDING GEAR ASSEMBLY (USING STRUT ASSEMBLY, PART NO. 3 3 1 4 2 0 3 3 AND 3316500-13)

-

PART NO. 33142053

THE INSTRUCTIONS CONTAINED IN PRECEDING SECTIONS OF THlS TECHNICAL MANUAL APPLY EXCEPT FOR THE DIFFERENCES LISTED IN THlS DATA SHEET

BUILDUP INSTRUCTIONS. Same as for part No. 396175-13, except as follows: Sheet 1is replaced by figure 6-19, sheet 1. Sheet 2 is replaced by figure 6-19, sheet 2. Sheet 3 is replaced by figure 6-19, sheet 3. Sheet 4 is replaced by figure 6-19, sheet 4. Sheet 5 is replaced by figure 6-19, sheet 5. Sheet 6 is replaced by figure 6-19, sheet 6. Sheet 7 is replaced by figure 6-19, sheet 7. Sheet 8 is replaced by figure 6-19, sheet 8. Sheet 9 is replaced by figure 6-19, sheet 9. b. Substitute index numbers from figure 6-19 for similar parts in figure 5-1. In subparagraphs that are changed or replaced, new index numbers have already been substituted in these instructions. c. In instructions: (1) Omit subparagraph (4). (2) In subparagraph (17) change torque value to 210 (+lo) foot-pounds. (3) After subparagraph (181, insert new subparagraph (18A): (18A) Install pin (11) in each of the upper trunnions of the steering cylinders. The pins are to be centered in the trunnions to within 0.03 inch. (4) After subparagraph (22), insert new subparagraphs (22A) and (22B): (22A) Loosen the nut (21) on the inner eyebolt (23). Position the bracket assembly (20) in place. Lift the inner eyebolt (23) to enable pin (24) with washers (22 and 25) to be inserted. Insert the pin (24). (22B) Retighten nut (211, making sure that the eyebolt (23) is correctly aligned and that the bracket assembly (20) is free to pivot.

(5) Replace subparagraph (23) with new subparagraph (23): (23) Install washer (25) and cotter pin (26) on pin (24). (6) Omit subparagraphs (26) and (27). (7) Replace subparagraph (28) with new subparagraph (28): (28) Install one side of the manifold (closest

to cylinder) with bolt (291, washer (371, washer (361, and nut (29). Install other side of manifold with bolt (33) through washer (361, spacer (35), support (341, washer (371, and nut (38). (8) Replace subparagraphs (38) through (42) with new subparagraphs (38) through (42):

(38) Install four packings (51) on four unions (52). (39) Install two of the unions (52) in each of the steering cylinders (10). (40) Lubricate the threads of the two unions and two elbows (55 and 58) on the inboard sides of manifold assemblies (28 and 32). (41) Install tube assembly (53). Tighten nut (54) on elbow (55). Tighten fittings on tube assembly. (42) Install tube assembly (56). Tighten nut (57) on elbow (58). Tighten fittings on tube assembly. (9) Replace subparagraph (48) with new subparagraph (48): (48) Insert adapter (72) and barrel nut (73) in recess of steering collar (6). Slip bracket (76) over steering collar (61, rod ends of steering cylinder (101, and seals (71). Attach with bolt (741, spacer (751, washer (781, and nut (79). Attach bracket (76) to adapter (72) using bolt (81) and washer (80). (10) Replace subparagraph (49) with new subparagraph (49):

T.O. 4S2-23-3

DIFFERENCE DATA SHEET

(49) Attach bracket (82) to fulcrum of strut washers (851, and two nuts (86).

(88) Pack wheel bearing assemblies (part of wheel and tire assembly) (146) with grease, Specification MIL-G81322.

(11) Replace subparagraph (51) with new subparagraph (51):

(89) Lubricate the axles with grease, Specification MIL-G81322.

(51) Attach brace assemblies (93 and 94) to the strut assembly (1).Install spacer (96) and nut (95) on the end of the pin having the longer threads. Tighten this nut against the shoulder of the pin. Install spacer (96) and nut (95) on the other end of the pin. Tighten this nut against the opposite end of the pin.

(90) Install collar (145) on each of the axles.

(1) using screw (83) in the forward position, two

(12) Replace subparagraphs (55) through (74) with new subparagraphs (55) through (57): (55) Install torque arm (103) with grease fitting forward. (56) Attach arm (103) with bolt (1021, two washers (101 and 104), and nut (105). (57) Tighten the nut (105) and install cotter pin (106). (13) Replace subparagraph (78) with new subparagraph (78): (78) Route the other end of the cable around collar pulley. Locate bracket (119) in position and determine the thickness of laminated shim (120) required to obtain a minimum clearance of 0.010 to 0.020 inch between the outer edge of the collar (6) and the bracket (119). Install the bracket (119) and shims ( 120) wet using corrosion-preventive sealant per Specification MIL-S-8802B2 on the faying surfaces. Secure in place by inserting two screws (121) through two washers (1221, collar (61, and support (123) and fastening with two washers (124) and two nuts (125). Before tightening the nuts, position the bracket (119) to provide the minimum vertical clearance obtainable (but not less than 0.020 inch) between the top of the collar (6) and the adjacent lower surface of the bracket (119). (14) Replace subparagraph (85) with new subparagraph (85): (85) Loosely install two pulleys (1371, two guard pins (139),four washers (1421, bolt (143), and nut (144) in the forward end of the bracket (82). Route the cables under the pulleys. Locate the guard pins (139) and tighten the nut (144). (15) Replace subparagraphs (87) through (97) with new subparagraphs (87) through (97): (87) Install thread protector, part No. 340714, or equivalent, on each of the axle threads.

(91) Place inboard bearing in each of the wheels, and assemble grease seal, washer, and retaining ring. (92) Place the wheels on the axles. (93) Remove the thread protectors. (94) Install the outer bearing assemblies and washers. (95) Tighten cap (149) until a bearing drag is noticed when spinning wheel by hand. Back cap off until closest lockscrew hole lines up with keyway. Tighten screw (150) until it bottoms out in bottom of keyway. Do not use any of the No. 10 holes in the piston assembly for lockscrew. A gap between screw head and cap is permissible. Lockwire the screw. (96) Cap exposed union (151) and four elbows (63, 64, and 152). (97) Lubricate all grease fittings with grease, Specification MIL-G-81322. (16) Add subparagraph (98): (98) Attach tang assembly to axle with four bolts (153 and 1561, four washers (154 and 1571, caps (155 and 1581, four washers (1591, and four nuts (160).

SUBASSEMBLY BUILDUP. Same as for part No. 396175-13, except as follows: a.

Figure 5-2 is replaced by figure 6-20.

b. In the instructions:

manifold

assembly

buildup

(1) Replace subparagraph (12) with new subparagraph (12):

(12) Install one of the packings (11)in the groove nearest to the shoulder of the valve body (1); behind the packing, install ring (12). (2) Replace subparagraph (14) with new subparagraph (14): (14) Install the third packing (11) in the outer groove of the valve body (1); in front of the packing, install ring (12).

DIFFERENCE DATA SHEEI'

(3) Replace subparagraph (16) with new subparagraph (16): (16) Instdl washer (14) and Spacer (151, and hold washers, spacer, and valve assembly in place with ring (16). (4) Replace subparagraphs (24) through (27) with new subparagraphs (24) and (25): (24) Install nut (25), ring (261, and packing (27) on each of two elbows (28). The nut (25) should be positioned such that the packing (27) fits into the groove in the elbow (28) and not on the screw threads. Lubricate with petrolatum, Federal Specification W-P-236. (25) Install elbows (28) in the manifold assembly (13). Tighten the nuts (25) finger tight. (5) Replace subparagraph (30) with new subparagraph (30): (30) Install washer (30) and spacer (311, then hold washer, spacer, and valve assembly in place with ring (32). (6) Replace subparagraphs (37) through (40) with new subparagraphs (37) and (38): (37) Install two packings (49) on two unions (50) and lubricate with petrolatum, Federal Specification W-P-236. (38) Install unions (50) in valve assembly (40) and tighten.

c. The cylinder and tubing assembly, part No. 396106-3, is built up in the same way as for part No. 396175-23, with the exception that new part numbers for the following index numbers in figure5-3 are as listed below: 3400770-7 CYLINDER ASSEMBLY KSU17-1 BALL 396122-3 BRACKET MS21924-6 UNION LS4634-6 GASKET LS4634-6 GASKET 697260-1 VALVE MS21902-6 UNION LS4634-6 GASKET MS21908-6 ELBOW LS4634-6 GASKET MS21902-6 UNION LS4634-6 GASKET MS21908-6 ELBOW 370740-345 TUBE ASSEMBLY 370740-347 TUBE ASSEMBLY

DIFFERENCE DATA SHEET

1. 2

3. 4. 5.

6. 7. 8. 9.

lo. 11. 12. 13.

33142053 STRUT ASSEMBLY 338948 SPACER. M A 1O 6 A BEAR1NG (2 REQD)

355844-1 RETAINER (2 REQD) KWB1!%SG BEARING (4 REQD) STEERING COLLAR (PART OF 1) NN(PARTOF1) BRACKET ASSEM8LY (PART OF 1) 356019-1 SPACER (4 REQD) 402306-3 !SEERING CYUNDER (2 REOD) NAS561P-14-16 PIN (2 REQD) 356176-1 SHIELD (2 REQD) MS16224-1050 RING (2 REOD)

TYPICAL BOTH STEERING CYUNOERS

Figure 6-19. Nose Landing GearAssembly, Part No. 3314205-3 (Sheet 1 of 9)

T.O. 452-23-3

DIFFERENCE DATA SHEW

14. 15. 16. 17. 18. 19. 20. 21. 22.

AN316-4R NLIT 354553-1 LINK END 345571 UNK END NAS334CPA13 BOLT AN960416 WASHER MS21042-4 NUT 339270-7 BRACKETASSEMBLY MS21042-5 N a (PART OF 1) AN960-516 WASHER (PART OF 1) n. ~ ~ 4 . 4 - E AEYEBOLT (PARTOF 1) 24. MS20392-3G51 PIN 25. AN960-416L WASHER (2 REQD) 26. MS24665-151 COTl'ER PIN 27. 351505 SPACER (2 REQD)

MANIFOLD ASSEMBLY (BUILT UP ON 372683-5, SEE FIGURE 6-20) NAs1304-18H BOLT (2 REQD) AN960W16 WASHER (2 REQD) MS21042-4 NUT (2 REQD) MANlFOLO ASSEMBLY (BUILT UP ON 3726843, SEE FIGURE 6-20) NAS1304-24 BOLT 3314342-15 SUPPORT NAS43004-16 SPACER 351506 WASHER AN960D416 WASHER (2 REQD) MS21042-4 NUT (2 REQD)

Figure 6-19. Nose Landing Gear Assembly, Part No. 3314205-3 (Sheet 2 of 9)

T.O. 452-23-3

DIFFERENCE DATA SHE=

39.

373531-5 VALVE ASSEMBLY (PART OF 28) 40. NAS1303-6D BOLT 41. AN960-10 WASHEA 42. AN310-3 NUT 43. MS24665-134 COlTER PIN 44. NAS1304-15H BOLT 45. AN960416L WASHER 46. AN960D416 WASHER 47. MS20219-4 PULLEY 48. 339272-2GUARD PIN (2 REOD) 49. 2752-048 NUT 50. LS4093-4 RETAINER 51. 3-906N168-80 PACKING (4 REOD) 52. MS219M-6 UNION (4 REOD) 53. 370740-417 TUBE ASSEMBLY 54. AN62894 NUT (SAME AS 25, FIGURE 6-20) 55. MS21907-4 ELBOW (SAME AS 28. FIGURE 6-20)

56. 57. 58.

59. 60. 61. 62 63. 64. 65.

370740-415 TUBE ASSEMBLY AN6289-4 NUT (SAME AS 25. FIGURE 6-20) MS21907-4 ELBOW (SAME AS 28. FIGURE 6-20) 370740-46 TUBE ASSEMBLY (2 REOD) AN6289-6 NUT (2 REOD. SAME AS 19 AND 33 FIGURE 6-20) MS2190&6 ELBOW (2 REOD SAME AS 22 AND 36. FIGURE 6-20) 37074047 TUBE ASSEMBLY (2 REOD) MS21908-6 ELBOW (SAME AS 61, FIGURE 6-20) MS21908-6 ELBOW (SAME AS 54. FIGURE 6-20) AN6289-6 NUT (2 REOD. SAME AS 51 AND 58. FIGURE 6-20)

Figure 6-19. Nose Landing Gear Assembly, Part No. 3314205-3 (Sheet 3 of 9)

T.O. 4S2-233

DIFFERENCE DATA SHEET

DIFFERENCE DATA SHEET 84 VLP,

88. 388089-1. -5 ARM ASSEMBLY 67. 356028-1 BOLT 68. AN96B1416 WASHER 59. -14 NUT 70. MS2COTIER PIN 71. 3!515165 SEAL ASSEMBLY (4 REQD) 72. -1 ADAPTER 73. 2752654 BARREL NUT 74. NASl#)S# BOLT (2 REQD) 75. --I SPACER 76. 403530-5 BRACKET ASSEMBLY 4035295 BRACKET ASSEMBLY (OPPO!3lE SIDE) T7. 3802013 SPACER 78. AN980816 WASHER (2 REQD)

79. MS21042S NUT (2 RmD)

&.-

AN980D516 WASHER M I 0 0 5 8 BOLT 339288 BRACKET NAS51747 SCREW E(AS517414 SCREW 85. AN960D416 WASHER (2 REQD) 86. MS21042-4 NUT (2 REQD) 80. 81. 82 83. 84.

81

Figure 6-19. Nose Landing Gear Assembly, Part No. 3314205-3 (Sheet 4 of 9)

Change 3 6-113

T.O. 4S2-23-3

DIFFERENCE DATA SHEET

87. 3961-5 CYLINDER AND TUBING ASSEMBLY 88. 371670-1 BOLT

89. 90. 91. 92.

392667 WASHER M m C 1 2 WASHER MS20002-12WASHER -627-126 NUT

93. 371689-8 BRACE ASSEMBLY 94. 3716847 BRACE ASSEMBLY 95. LW640.164 NUT (2 REQD) 96. 756001-1SPACER 97. 345731 SPACER 98. MS16624-1200RING (2REQD) 99. KSSB-32-2 BEARING (2 REQD, L/R)

Figure 6-19. Nose Landing Gear Assembly, Part No. 3314205-3 (Sheet 5 of 9)

T.O. 4S2-23-3

DIFFERENCE DATA SHEET

DIFFERENCE DATA SHEET

6

100. 101. 102. 103.

JACK P U G (PART OF 1) AN960-1416 WASHER 3302201-1 BOLT 388068-1, -5 TORQUE ARM

104. AN-1 416L WASHER 105. A N S I 4 NUT 106. MS24665-359COTTER PIN

\

Figure b19. Nose Landing Gear Assembly, Part No. 3314205-3(Sheet 6 of 9)

Change 3 6-ll5

T.O. 452-23-3

DIFFERENCE DATA SHEET

,1 (REF)

113 (LONGER END)

125 TOP VIEW 107. 108. 109. 110. 111. 112 113. 114. 115-

344069-3 CAP 355327-3 HANDLE ASSEMBLY NASllWl8D BOLT AN3104 NUr 355326-1 BOLT MS24665-134 COTTER PIN 339271 CABLE ASSEMBLY MS24665-132 COTER PIN (2 REQD) NAS42HT-6-32 SPACER

116 NAS603-18P SCREW 117. AN960-10L WASHER 118. MS21042-3 NUT 119. 3392863 BRACKET 120- LS5940-3 LAMINATED SHIM 121. NAS623-314SCREW (2 REQD) 122 NASll97-10WAWER (2 RMD) 123- 3314342-13 SUPWRT 124- AN960-C10L WAWER (2 REQD) 125. MS21042-3 NUT (2 REQD)

Figure 6-19. Nose Landing Gear Assembly, Part No. 3314205-3 (Sheet 7 of 9)

T.O. 4S2-23-3

DIFFERENCE DATA SHEET

2752-048 NUT

MS20219-4 P U U W 339272-3 GUARD PIN (2 REQD) AN960D416 WASHER AN960-416L WASHER NAS1304-15H BOLT 339272-3 GUARD PIN (2 REQD) AN960D416 WASHER AN960-416L WASHER 2752-048 NUT (2 REQD) LS4893-4 RETAINER (2 REQD) MS20219-4 PULLEY (4 REQD) AN9600416 WASHER (2 REQD) 339272-3 GUARD PIN (6 REQD) AN960D416 WASHER (2 REQD) NAS1304-1SH BOLT (2REQD) AN960-416L WASHER (4 REQD) NAS11W32D BOLT AN320-4 NUT

Figure 6-19. Nose Landing Gear Assembly, Part No. 3314205-3 (Sheet 8 of 9)

T.O. 4S2-23-3

DlFFERENCE DATA SHEET

145. 337119 COLLAR (2 REOD) 146. 339242-27WHEEL AND TIRE ASSEMBLY (2 REQD) 147. 5866-L12 SEAL (2 REQD) 148. 3314206-1 RETAINER 149. 3329347-1 CAP 150. 361806-1 SCREW 151. MS21902-6 UNION (PART OF 87) 152. MS21908-6 ELBOW (2 REQD, PART OF 87)

153. 154. 155. 156. 157. 158. 159. 160.

NASI106-9BD BOLT (2 REOD) AN960-616L WASHER (2 REQD) 33293482 CAP NAS1106-86D BOLT AN960-616L WASHER (2 REQD) 3329348-1 CAP AN96@616LWASHEFI (4 REOD) MS21042-6 NUT (4 REQD)

Figure 6-19. Nose Landing Gear Assembly, Part No. 3314205-3 (Sheet 9 of 9)

T.O. 452-233

DIFFERENCE DATA S H E D

BUILDUP OF MANIFOLD ASSEMBLY ON 372684-3

Figure 6-20. Manifold Assemblies for Part No. 3314205-3 (Sheet 1 of 3)

T.O. 482-23-3

DIFFERENCE DATA SHEET

BUILDUP OF M A N I F O L D ASSEMBLY 0 N 372683-5

Figure 6-20. Manifold Assemblies for Part No.3314205-3(Sheet 2 of 3)

T.O. 4S2-23-3

DIFFERENCE DATA SHEET

1. 2. 3. 4. 5. 6. 7. 8. 9. 10.

ii. 12. 13. 14. 15. 16. 17. 18.

3 7 2 6 9 0 3 VALVE BODY ( 2 REQD) 356356-1 VALVE ( 2 REQD) 337452 SPRING ( 2 REQD) 351514 RETAINER ( 2 REQD) 3-908N16880 PACKING ( 2 REQD) AN814-8DL PLUG ( 2 REQD) M S 2 8 7 7 5 0 0 8 PACKING (2 REQD) 351502 PLUG ( 2 REQD) NAS561P3-16 PIN ( 2 REQD) 351503-3 RlNG ( 2 REQD) M S 2 8 7 7 5 2 2 2 PACKING ( 6 REQD) LS456527 RlNG (8 REQD) 3726684-5 MANIFOLD ASSEMBLY 351505 WASHER 3511505 SPACER M S 1 6 6 3 4 1 1 7 5 RlNG 3-903N168-80 PACKING ( 2 REQD) A N W D L PLUG ( 2 REQD)

19. 20. 21. 22. 23. 24. 25. 26. 27.

28. 29. 30. 31. 32. 33. 34. 35. 36. 37. 38. 39.

AN6289-6 NUT MS28773-06 RlNG 3-906Nl68-80 PACKING MS21908-6 ELBOW 3-906Nl68-80 PACKING M521902-6 UNION AN628994 NUT ( 2 REQD) MS28773-04 RlNG ( 2 REQD) 3-904N168-80 PACKING ( 2 REQD) M S 2 1 9 0 7 4 ELBOW ( 2 REQD) 372683-5 MANIFOLD ASSEMBLY 351506 WASHER 351505 SPACER MS16624-1175 RlNG AN6289-6 NUT MS28773-06 RlNG 3-906N168-80 PACKING MS21908.6 ELBOW 3-906N168-80 PACKING MS21902-6 UNION MS28775.113 PACKING ( 2 REQD)

40. 41. 42. 43. 44. 45. 46. 47. 48. 49. 50. 51. 52. 53. 54. 55. 56. 57. 58. 59. 60. 61.

373531-7 VALVE ASSEMBLY MS20005.34 BOLT ( 2 REQD) MS20002C5 WASHER ( 2 REQD) AN960516 WASHER (2 REQD) 5758S524 NUT ( 2 REQD) M 5 2 0 0 0 5 2 8 BOLT 345570 WASHER AN960516 WASHER 5 7 5 8 5 5 2 4 NUT 3-904N168-80 PACKING MS21924-4 UNION ( 2 REQD) AN6289-6 NUT MS28773-06 RlNG 3-906N168-80 PACKING MS21908.6 ELBOW 3-906N168-80 PACKING MS21902-6 UNION AN6280-6 VALVE AN6289-6 NUT MS2877346 RlNG 3-906N168-80 PACKING MSU908.6 ELBOW

Figure 6-20. Manifold Assemblies for Part No. 3314205-3 (Sheet 3 of 3)

6-121/(6122blank)