Service Bulletin: Cfe738 Turbofan Aircraft Engine

 

CFE738 TURBOFAN AIRCRAFT ENGINE

SERVICE BULLETIN CFE Company

ALERT ENGINE - TURBINE SECTION - BORESCOPE INSPECTION OF THE STAGE 2 HIGH PRESSURE TURBINE (HPT) ROTOR DISK AFT FACE FOR CONTACT RUBS WITH THE STAGE 1 LOW PRESSURE (LP) TURBINE/NOZZLE ASSEMBLY 1.

Plann nnin ing g Inf Info orm rma ati tio on A.

Effectivity This service bulletin is applicable to the following turbofan aircraft engines. Part No.

Model No.

Serial No.

Application

3050000-5

CFE738-1-1B

105106 thru 105111, 105114 thru 105119, 105121 thru 105124, 105126, 105127, 105132, 105133,

Falcon 2000

105135 thru 105139, 105141 thru 105144, 105146 thru 105150, 105153, 105162, 105164 thru 105168, 105170 thru 105173, 105176 thru 105182, 105184, 105185, 105189, 105191, 105196, 105199, 105203, 105219, 105222, 105223, 105239, 105254, 105259, 105260, 105263, 105265, 105269, 105271, 105272, 105275

Aug 18/98 Copyright 1998 CFE Company

CFE738-A72-8028 Page 1 of 6

 

CFE738 TURBOFAN AIRCRAFT ENGINE

SERVICE BULLETIN CFE Company

1.

B.

C.

Reason (1)

Problem: Proble m: Con Contac tactt rubs rubs on on the sta stage ge 2 HPT HPT rotor rotor dis disk k aft aft face face from from cont contact act wit with h the the forward face of the seal on the stage 1 LP turbine/nozzle assembly was observed during the disassembly of a CFE engine. The rub if left uncorrected could result in an uncontained turbine rotor separation.

(2)

Backgroun Backgr ound: d: The stat static ic seal seal carr carrier ier on Engine Engine,, Seria Seriall No. No. 105156 105156,, was was found found to to be distorted, which allowed contact with with the stage 2 HPT rotor disk after assembly. assembly. The seal distortion was determined to have occurred during a previous disassembly d isassembly,, as the No. 4 bearing support was removed from the engine.

(3)

Action:: Thi Action This s servic service e bullet bulletin in requir requires es a bores borescop cope e inspec inspectio tion n of the the stage stage 2 HPT HPT rotor rotor disk aft face to identify engines that have contact rub and remove those engines from service to replace the damaged parts.

Description This service bulletin provides instructions for the borescope inspection of the stage 2 HPT rotor disk aft face.

D.

Compliance CFE Company recommends that this service bulletin be accomplished within 60 days after receipt of this service bulletin. This service bulletin may be complied with with as part of scheduled engine inspections by operators that are nearing the 600 hour Minor Inspections or the 1200 hour Borescope Inspections.

E.

Approval FAA approved.

F.

Man Ma nho hour ur Re Requi uirrement nts s An estimated 30 manhours is required to access the engine and return it to service following the borescope inspection.

G.

Mater Mat erial ial - Pric Price e and and Avai vailab labili ility ty A warranty program is available for this modification, provided this inspection is done with the supervision of CFE personnel, and compliance recommendations of Paragraph D are met.

H.

Tool ooling ing - Pric Price e and and Av Avai ailab labili ility ty No special tooling is required except that already listed in publications referenced in Paragraph J.

I.

Weight and Balance No change.

Aug 18/98

CFE738-A72-8028 Page 2

 

CFE738 TURBOFAN AIRCRAFT ENGINE

SERVICE BULLETIN CFE Company

1.

J.

Publications References The sources of information used in the preparation of this service bulletin include CFE Company engineering documentation and the following. Heavy

Light

Illustrated

Part/  Model No.

Maintenance Manual

Maintenance Manual

Parts Catalog

CFE738-1-1B

72-06-04

*72-06-03

*72-06-01

*Affected Chapter/Section/Subject 72-00-00, Inspection, 72-50-06 and 72-50-08.

K.

Serv Se rvic ice e Bul Bulle leti tin n Ref Refer eren ence ces s None.

L.

Othe Ot herr Pu Publ blic icat atio ions ns Af Affe fect cted ed Same as those listed under Paragraph J, Publications References.

Aug 18/98

CFE738-A72-8028 Page 3

 

CFE738 TURBOFAN AIRCRAFT ENGINE

SERVICE BULLETIN CFE Company

2.

Acco Ac comp mpli lish shme ment nt In Inst stru ruct ctio ions ns NOTE: Publications Publications liste listed d in Section Section 1 provide provide applicabl applicable e disassembl disassembly y, cleaning, cleaning, inspection, reassembly, reassembly, and testing instructions and shall be referred to during the accomplishment of the following instructions. Borescope inspection must be accomplished CFE Product Support Engineering. Some training in is coordination necessary to with insure accuracy of the inspection.

A.

Perform Perf orm Bores Borescope cope Insp Inspecti ection on of the Stage Stage 2 HPT Rotor Disk Aft Face Face (1)

Remove the Remove the aircra aircraft ft compo componen nents ts neces necessar sary y to acces access s the stag stage e 1 LP turbin turbine/n e/nozz ozzle le assembly on the engine. Refer to the Aircraft Aircraft Maintenance Manual.

(2)

Disconnec Discon nectt the aft aft stage stage 3 coolin cooling g metal metal tube tube assemb assembly ly from from the the either either the the left left hand or or right hand side stage 3 buffer air manifold. manifold. Refer to 75-20-01, Removal, Removal, Figure 301, 301, in the Light Maintenance Manual.

NOTE: NOT E: (3)

The view view of of the engi engine ne in 75-2 75-20-0 0-01, 1, Remov Removal, al, Figure 302 , in the Light Maintenance Manual, is forward looking aft.

Remove the Remove the left left hand hand or right right hand hand side side (aft (aft looking looking forwa forward) rd) stag stage e 3 buffer buffer air air coolin cooling g manifold from the engine. Refer to 75-20-01, Removal, Figure 302 , in the Light Maintenance Manual.

NOTE: Removal Removal of the air air transfer transfer tube assemb assembly ly located located at the the 12 o’cloc o’clock k position in the stage 1 LP turbine/nozzle assembly allows easier installation of the borescope. Removal of an air transfer tube assembly from another location in the stage 1 LP turbine/nozzle assembly is acceptable if the air transfer tube assembly located at the 12 o’clock position cannot be removed. (4)

Remove the Remove the air tran transfe sferr tube asse assembl mbly y locate located d at the 12 12 o’clock o’clock posi positio tion n in the stag stage e1 LP turbine/nozzle assembly. assembly. Refer to 75-20-01, Removal, Figure 302 , in the Light Maintenance Manual.

(5)

Remove the Remove the cover cover from from the forw forward ard face face of the the perman permanent ent magn magnet et altern alternato atorr (PMA) (PMA) to allow rotating of the HP spool from the square drive in the rotor shaft of the PMA. Refer to 72-00-00, Inspection, in the Light Maintenance Manual.

(6)

Insert the Insert the boresc borescope ope into into the the stage stage 3 coolin cooling g hole at at 12 o’cloc o’clock k positi position on (or othe otherr localocation) in the stage 1 LP turbine/nozzle assembly.

(7)

Guide the Guide the boresc borescope ope tip tip forwa forward rd until until the the aft aft face face of the the the stag stage e 2 HPT roto rotorr disk disk is visible.

Aug 18/98

CFE738-A72-8028 Page 4

 

CFE738 TURBOFAN AIRCRAFT ENGINE

SERVICE BULLETIN CFE Company

Stage 2 HPT Rotor Disk Aft Face Borescope Inspection Figure 1 Aug 18/98

CFE738-A72-8028 Page 5

 

CFE738 TURBOFAN AIRCRAFT ENGINE

SERVICE BULLETIN CFE Company

2.

A.

(8)) (8

Visual Visu ally ly in insp spec ectt rad radia iall lly y the the st stag age e 2 HP HPT T rot rotor or di disk sk af aftt fac face e for for co cont ntac actt rub rubs s wit with h the the forward face of the seal on the stage stage 1 LP turbine/nozzle assembly. assembly. Rotate the HP spool of the engine to allow 360 degree inspection of the stage 2 HPT rotor disk aft face. (See Figure 1.) NOTE: When the the borescope borescope inspectio inspection n is performed performed at at customer’s customer’s base, base, one ferry flight to a CFE Service is allowed when the borescope inspection results indicateCenter an engine exchange is required.

(9) (10)) (10

(11) (1 1)

3.

(a)

If cont contact act rubs are obse observe rved d on the the stage stage 2 HPT rot rotor or disk disk aft aft face face,, the the engine engine must be reassembled, then removed from the aircraft and returned to a Heavy Maintenance Facility for repair. repair. Contact Product Support Engineering.

(b)

If no no contac contactt rubs rubs are are observ observed ed on the sta stage ge 2 HPT HPT roto rotorr disk disk aft aft face, face, mak make e an engine log book entry of compliance with this service bulletin.

Remove Rem ove bor boresc escope ope fro from m the the stage stage 1 LP tur turbin bine/n e/nozz ozzle le asse assembl mbly y. Installl the air Instal air transf transfer er tube tube assemb assembly ly with with a new meta metalli llic c gasket gasket in in the stage stage 1 LP turbine/nozzle assembly. assembly. Refer to 75-20-01, Installation, in the Light Maintenance Manual. Installll the cover on the forwa Insta forward rd face of the perman permanent ent magne magnett altern alternator ator (PMA) (PMA).. Refer to 72-00-00, Inspection, in the Light Maintenance Manual.

(12)

Install the Install the left left hand hand or or right right hand hand side side (aft (aft looki looking ng forward forward)) stage stage 3 buff buffer er air air cooling cooling manifold on the engine. Refer to 75-20-01, Installation, Installation, in the Light Maintenance Manual.

(13)) (13

Connectt the aft Connec aft stage stage 3 coolin cooling g metal metal tube tube assemb assembly ly to the the left left hand hand or right right hand hand side side stage 3 buffer air manifold. Refer to 75-20-01, Installation, Installation, in the Light Maintenance Manual.

(14)) (14

Installl the aircr Instal aircraft aft comp compone onents nts remo removed ved to to access access the the stage stage 1 LP turb turbine ine/no /nozzl zzle e assembly on the engine. Refer to the Aircraft Aircraft Maintenance Manual.

(15)) (15

Check and Check and ensure ensure proper proper engi engine ne operat operation ion in acco accorda rdance nce with with Airc Aircraf raftt Flight Flight Manua Manuall and/or appropriate aircraft documents.

(16)) (16

Make entry Make entry in engine engine log log book noti noting ng date date of compl complian iance, ce, engi engine ne operat operating ing time time (and (and serial number of installed component if applicable) and compliance with this service bulletin (and service bulletin revision number if applicable).

(17) (1 7)

Reid Re iden enti tifi fica cati tion on of of equi equipm pmen entt is not not req requi uire red. d.

(18)) (18

Complete Comple te Compl Complian iance ce Certi Certific ficate ate form form and and mail. mail. Con Contac tactt local local CFE CFE compan company y authoauthorized service center to obtain forms, if required.

Mate teri ria al Inf Info orm rma ati tio on Not Applicable

Aug 18/98

CFE738-A72-8028 Page 6