HoneyweII
MAINTENANCE MANUAL GAS TURBINE ENGINE
MODEL NO. T53-L-703
PARI NO. 1-000-060-23
MARCH 30,1990 REVISION 2, SEPTEMBER 30, 2002
DlQltil^sign ed bvJ3ite
Muñes M C^N: ehfeJaito Muñoz
M, ernát^taatin£e4nsz
REPORT NO. 290.2
HoneyweII
HoneyweII Engínes Phoenix, Arizona
TO; HOLDERS OF GAS TURBiNE ENGINE MAINTENANCE MANUAL REPORT NO. 290.2 DATED September 30, 2002 THiS REVtSED PUBLICATION IS ISSUED FOR USE IN SUPPORT OF THE FOLLOWING AIRCRAFT. ENGINE PART NO
ENGINE MODELNQ.
AIRCRAFT APPLICATION
1-000-060-23
T53-L-703
Bell AH-1 Series Bell UH-1 Series
REVtSION NO. 2 DATED SEPTEMBER 30. 2002 This is a COMPLETE reissue. Due to the extent of the changes involved in this revisión, this publication has been repnnted in its entirety. Piease remove and discard all pages of prior issues and replace with this issue. Temporary Revlsions 2 through 70 are incorporaled in this issue.
Inquires regarding distribution of this publication should be directed to: HoneyweII Aerospace Services Data Distribution, M/S 26-08/2101-201 P.O. Box 52170, Phoenix. AZ 85072-2170 Teiephone: (602) 365-2493, FAX: (602) 365-5577 or (602) 365-2832 Inquires of a technical nature regarding this publication should be directed to: HoneyweII Engines, Systems & Services Customer Information Center Attn: Dept 66-20/503-218 P.O. Box 52181, Phoenix, AZ 85072-2181 Teiephone: 1-800-338-3378, FAX: (602) 231-2481 HIGHLIGHTS All references to AlliedSignal Engines were changed to HoneyweII Engines, Systems & Services. All table of contents revised to reflect changed pages and to incorpórate TR 30 through 43. All figure keys revised from single column to double column. All list of effective pages revised to reflect changed pages. All consumables were checked and updated as required. Chaoter/Section/Pages
Descriotion of Chanae
Record of Revisions
Updated to reflect current revisión.
Record of Temporary Revisions
Updated to reflect current temporary revisions.
REPORT NO. 290.2-HIGHLIGHTS
Page 1 of 9 Sept 30/02
HoneyweII
HoneyweII Engines Phoeníx, Arizona
Chaoter/Section/Panes
Descriníion nf Ohanae
Service Bulletin List
Updated to reflect current builetins.
70-45-01 All Pages Deleted all data and placed in Standard Practices Manual. 71-00-00 Page 1
Incorporaled TR 8 to revise paragraph 2.A.(1) WARNING and NOTE.
Page 5
Incorporaled TR 65.
Pages 7 and 8
incorporated TR 19 and 20.
Page 10
Incorporated TR 61.
Page 11
Changed 75-10-2 to 75-10-02 and 73-20-1 to 73-20-01 in steps (4) and (5). Added chip detector to step C.(2).
Page 12
Revised steps D.(4), (5) and (6). Changed tool kit part numbers step E. Added NOTE, changed tool kit part number and contents and deleted steps (a), (b) and (c).
Page 13 Page 15
Deleted steps (1)(d) and (i). Deleted filter inspection part numbers steps (2) and (3). Deleted step (4) entirely.
Page 16
Revised step (5).
Pages 26 through 40
Added new procedures.
72-00-00 Page 1
Incorporated editorial notes.
Page 3
Revised table for fuel and oil type.
Page 18
Revised Figure 8.
Page 117
Editorial changeto step D.(2)(b).
Page 201
Deleted tool number in Table 201.
Pages 209 through 218
Incorporated TRs 50, 56, 58, 66, 67 and 68.
Page 217
Incorporated TR 26 altérnate cleaning Solutions.
Page 305
Revised part number is step (3)(a)-
REPORT NO. 290.2-HIGHLIGHTS
HoneyweII Chanter/Sfirtinn/PaoRs
HoneyweII Engínes Phoenix, Arízona
Descriotion of Channe
Pages 312 and 313
Editorial changes to step l.(1)(e) and added altérnate method.
Page 401
Revised Item reference in NOTE.
Page 405
Editorial changes to steps (15) and (19).
Page 410
Revised paragraph 6.A.(3)(e) reference to paragraph. Editorial changes to paragraph 7.B.{4) and (5).
Page 411
Revised torque valué in step (12).
Pages 601 through 614 and 616
Incorporated TR 3.
Pages 618, 619 and 620
Incorporated TR 9.
Page 621
Added reference to step (6)(a).
Pages 623 and 624
Incorporated TR 44,
Pages 629 and 630
Incorporated TR 63.
Page 701
Incorporated TR 45.
Page 702
Incorporated TR 46.
Page 703
Incorporated TR 47.
Page 705
Incorporated TR 48.
72-10-01 Page 208
Added seáis into torquemeter cylinder.
Page 209
Incorporated TR 58.
Page 219
Revised step (7)(b). Incorporated correct type of gloves tn WARNING.
72-30-01 Page 203
Revised step procedures for step B-(3).
Page 204
Revised procedures for steps B.(4) and (5).
Page 208
Incorporated 3.A-(1)(d) revised step procedures.
Page 211
Deleted CAUTION and steps A.{2). (3) and (4).
72-30-02 Page 201 Page 203
Incorporated editorial revisions in paragraph 1.A.(4) and NOTE. Deleted step B,(4).
REPORT NO. 290.2-HIGHLIGHTS
Page 3 of 9 Sept 30/02
HoneyweII Chaoter/Sertinn/Paofis
HoneyweII Engines Phoenix, Arizona Desr.rinlinn of Channe
Page 211
Incorporated TR 59 and revised step (e).
Page 216
Incorporated TR 24.
Page 222
Revised step (c)4.
Page 224
Revised step (4),
Page 226
Revised step (9).
Page 227
Revised blade limits in Figure 213.
72-40-00 Page 1/2
Revised Description and Operation procedure.
Page 204
Incorporated TR 25.
Pages 207 and 209 Page 209
Page 211 Page 212
Page 213 Page 215
Incorporated TR 23 and deleted associated figures. Revised reference to Figure 207 in step (3) and deleted Figure 207. Revised text within first and third CAUTION. Incorporated TR 27 to add steps (22), (27) and NOTE Revised step (23). Revised step B.(28). Incorporated TR 6 to add steps (1) and (6). Revised Ítem reference in step (5).
Page 216
Incorporated TR 4.
Page 217
Incorporated TR 5 to reflect changes to Figure 209.
Page 218
Incorporated TR 5.
Page 220
Revised step (I0)(f).
Page 226
Revised text in CAUTION.
Page 227
Deleted steps (49) and (50). Incorporated TR 7.
Page 230
Revised step (8).
72-40-01 Page 203 72-40-02 Page 201
Deleted steps (1) through (4). Added paragraph 1.B.(6)-
REPORT NO. 290.2-HIGHLIGHTS
Page 4 of 9 Sept 30/02
HoneyweII Chaoter/Section/Panes Page 202 72-40-03 Page 201
HoneyweII Engines Phoenix, Arízona
Descriotion of Chanae Revised Fjgure 201.
Deleted CAUTION folíowing step B.(1).
72-40-04 Page 203
Incorporated TR 13 deleting Figure 202, Sheet 1.
Page 207
Deleted steps (8) and (9).
Page 208
Deleted Figure 204.
Page 209
Revised Figure 205 tille part number.
Page 210
Deleted Figure 206.
72-40-05 Pages 201/202 72-40-06 Page 201
Deleted Figures 201, 202, 203 and step (3).
Incorporated TR 16.
Page 203
Incorporated TR 17.
Page 204
Deleted Figure 203 and paragraph 3.A.
72-40-07 Page 201 Revised paragraph 1.A.{1) and deleted Figure 201. Deleted paragraph 3.A and Table 201. 72-40-08 Page 201 Added Fahrenheit temperatura to step B.(1) and B(1)(a). Changed step in B.(1){b) from 50VDC to 250VDC. 72-50-03 Page 201
Incorporated TR 51.
Page 203
Incorporated TR 52.
Page 204
Incorporated TR 53.
Page 205
Incorporated TR 54.
Page 206
Incorporated TR 55.
72-50-04 Page 208
Deleted NOTE prior to step (17).
REPORT NO. 290.2-HIGHLIGHTS ÍSS
HoneyweII Chanfer/SRCtion/Panfts 72-51-00 Page 201
HoneyweII Engínes Phoeníx, Arizona Descrinfinn nf Channe
Revisad measurement in step (3).
Page 202
Incorporated TR 18.
Page 206
Incorporated TR 14.
Page 207
Revised material reference in step (21).
Page 208
Changed part number in step (a).
Page 214
Revised Figure 206.
Page 216
Incorporated TR 15.
72-51 -01 Page 201 Revised step A.(3) to add fluorescent penetran! inspection reference. Page 206
Added part number to step (2).
Page 207
Deleted part number from figure title.
Page 210
Deleted steps (5), (6) and (11) Revised steps (7), (9) and (10).
Page 211
Revised NOTE following paragraph 3.A.(1).
72-51-02 Page 201
Revised paragraph l.A.(6).
72-51-04 Page 201
Revised third bullet in NOTE following step A.
Page 205
Revised step (5).
Page 208
Revised Figure 205.
Page 209
Revised steps A.(7), (11). (12) and (13) to nozzle curl. Deleted paragraph 3 entirely and associated figures.
Page 210
Revised figure title.
72-51-05 Page 201 Deleted steps A.(2), (3), (4), entire step (6) and Figure 201. Revised step (5) (e). 72-60-01 Pages 201 and 203
Revised step A.{2). Corrected nomenclatura of ítem (14) in steps A.(11), B.(1), (2) and Key to Figure.
REPORT NO. 290.2-HIGHLIGHTS
Page 6 of 9 Sept 30/02
HoneyweII ChaDTfir/Section/Panfts
HoneyweII Engines Phoenix, Arizona Deserintinn of Channe
Page 207
Revised NOTE following step (4)(a).
Page 209
Added NOTE tollowing step (5)(b). Revised step (6)(b).
Page 210
Revised step (k).
Page 214
Revised steps (ab) and (ad).
Page 215
Added new step (ap).
73-10-01 Page 204
Revised text to paragraph 3.
73-10-02 Page 204
Deleted NOTE following steps A and (3)(d).
73-10-05 Page 202 Revised text to paragraph 3 and deleted paragraph 4,A.(1), 73-10-07 Page 201
Revised step A. (6).
Page 204
Added new step B.(4).
Page 205/206
Revised consumable in paragraph 3.A.(1) and deleted paragraph 4.A.(4).
73-20-01 Page 201
Incorporated TR 64.
Page 208
Revised paragraph 3.A.(1). and deleted step (2)(b).
Page 210
Incorporated TR 28.
Page 211
Incorporated TR 29.
Page 213
Incorporated TR 69.
Pages 213 and 214
Incorporated TR 70.
Page 215
Deleted Figure 205.
73-20-03 Page 205/206 74-20-01 Page 201
Revised consumable in paragraph 3.A-(1). Revised text in paragraph i.A.(l) and B.í3).
REPORT NO. 290.2-HIGHLIGHTS
Page7 of 9 Sept 30/02
HoneyweII Chantfir/SfiCfinn/PanRS 75-30-01 Page 204
75-30-03 Page 1 75-30-03 Page 203
77-20-01 Page 1 77-20-01 Page 201 Page 203
79-20-01 Page 201 Page 202 79-20-02 Page 201 79-20-03 Page 205
79-20-04 Page 201 79-20-07 Page 201
Descriotion nf Chanoe
Corrected misspelled word in step C.(4).
Pages 207 and 209 75-30-02 Page 201
HoneyweII Engines Phoenix, Arizona
Editorial change to step (8).
Added text to step (7).
Revised text to paragraph 1. Revised text in step A.(1} and NOTE prior to step
Revised text to paragraph 1.
Deleted paragraph 4 and associated figures. Added paragraph 5 title and revised steps (2), (3) and (4).
Added text to steps A.(2) and (6). Added step B.(2A). Revised Figure 201.
Revised step B.(2).
Added address to NOTE following step (7). Added vendor address to NOTE following paragraph 4-A.(1).
Revised part number in NOTE following paragraph 2.B.
Revised text in steps (3), (4), (6), (7) and (11).
Page 204
Revised text in step A.(12).
Page 206
Revised consumable in text following paragraph 3.A.
REPORT NO. 290.2-HIGHLIGHTS
Page 8 of 9 Sept 30/02
HoneyweII Chantar/ñartinn/Panas 79-30-02 Page 201
HoneyweII Engines Phoenix, Arizona Dasnrintion nf Ohanne
Revised text following paragraph 3.A,
80-00-00 Page 1
Added paragraph 1 and revised NOTE following component listing.
80-00-01 Page 401
Revised work stand part number in step (1).
Page 411
Incorporated TR 10.
Pages 414 and 415
Incorporated TR 11.
Page 418
Incorporated TR 12.
80-00-02 Page 401
Revised work stand part number in step (1).
Page 402
Deleted CAUTION preceding step B.(2).
80-00-03 Page 401
Revised work stand part number in step A.(1).
80-00-04 Page 401
Revised work stand part number in step A.(1).
Page 405
Deleted Figure 3.
Page 408
Revised NOTE following step D.{9).
Page 412
Editorial change to steps (4) and (7).
Page 413
Incorporated TR 60.
Pages 417 through 420
Revised Figure 6 and key to figure.
Pages 424, 425 and 426
Replaced steps M and N and added Figure 7A.
Page 432
Deleted CAUTION following step (5) and incorporated TR 57.
Page 436
Incorporated TR 57 and 62 and added step (27).
Page 437
Revised NOTE prior to step (29).
REPORT NO. 290.2-HIGHLIGHTS
Page 9 of 9 Sept 30/02
HoneyweII
MAINTENANCE MANUAL T53-L-703
SAFETY ADVISORY WARNING: BEFORE USING ANY OF THE MATERIALS CALLEO OUT iN THIS PUBLICATION, BE AWARE OF ALL HANDLING, STORAGE AND DISPOSAL PRECAUTIONS RECOMMENDED BY THE MANUFACTURER OR SUPPLIER. FAILURE TO COMPLY WITH THE MANUFACTURERS OR SUPPLIER RECOMMENDATIONS MAY RESULT This publicatfon!Ndescribes physica) andOR Chemical processes which may require the use of Chemicals, solvents, PERSONAL INJURY DISEASE. paints ands other commercially available materials. The user of this publication shouid obtain the Material Safety Data Sheets {OSHA Form 20 or equivalent) from the manufacturers or suppliers of the materials to be used. the user must become completeiy familiar with the manufacturer/suppliers information and adhere to the procedures, recommendations. warnings and cautions set forth for the safe use, handiing, storage and disposal of the materials.
WARRANTY/LIABILITY ADVISORY WARNING: HONEYWELL ASSUMES NO RESPONSIBILITY FOR ANY HONEYWELL EQUIPMENT WHICH iS NOT MAINTAINED AND/OR REPAIR IN ACCORDANCE WITH HONEYWELL’S PUBLISHED INSTRUCTiONS AND/OR HONEYWELL’S FAA/SFAR 36 REPAIR AUTHORIZATION, NEITHER DOES HONEYWELL ASSUME RESPONSIBILITY FOR SPECIAL TOOLS AND TEST EQUIPMENT FABRICATED BY COMPANIES OTHER THAN HONEYWELL. IMPROPERLY REPAIRED OOMPONENTS MAY BE INFERIOR AND MAY AFFECT AIRWORTHINESS OR REDUCE THE USEFUL LIFE OF THE COMPONENTS. IMPROPERLY FABRICATED SPECIAL TOOLING OR TEST EQUIPMENT MAY RESULT IN DAMAGE TO PRODUCT COMPONENTS OR PROVIDE ERRONEOUS RESULTE. WHEN USED, EQUIPMENT OR PARTS THAT HAVE BEEN REPAIRED OR FABRICATED BY OTHER THAN HONEYWELL AUTHORIZED FACILITES MAY INCREASE RISKS OF DEATH OR PERSONAL INJURY. COMPONENT FAILURES AND SECONDARY DAMAGE AND MAY VOID ANY WARRANTIES UNDERWRITTEN BY HONEYWELL. THIS MANUAL APPLIES ONLY TO ENGINE AND COMPONENTS MAINTAINED IN ACCORDANCE WITH HONEYWELL ENGINES, SYSTEMS & SERVICES APPROVED PROCEDURES USING HONEYWELL APPROVED PARTS. ALL INSPECTION, REPAIR AND OVERHAUL PROCEDURES PUBLISHED BY HONEYWELL, INCLUDING PART RETIREMENT UFE, ARE BASED SOLELY ON THE USE OF HONEYWELL PARTS THAT HAVE BEEN MAINTAINED USING HONEYWELL APPROVED DATA. THE DATA PUBLISHED HEREIN OR OTHERWISE SUPPLIED BY HONEYWELL IS NOT APPLICABLE TO NON-HONEYWELL PARTS OR PARTS THAT HAVE BEEN REPAIRED USING DATA AND/OR PROCESSES NOT APPROVED BY HONEYWELL. SAFETY WARRANTY/LIABILITY HONEYWELL IS NOT RESPONSIBLE FOR ANY PARTADVISORY OTHER THAN THOSE THAT IT HAS APPROVED.
290.2
Page 1 Sept 30/02
HoneyweII
MAINTENANCE MANUAL T53-L-703
BEFORE PERFORMING ANY PROCEDURE CONTAINED IN THIS MANUAL YOU MUSI INSPECT THE AFFECTED PARTS AND RECORDS FOR EVIDENCE OF ANY MANUFACTURE, REPAIR, REWORK OR USE OF A PROCESS NOT APPROVED BY HONEYWELL, IF YOU IDENTIFY OR SUSPECT THE USE OF PARTS NOT AUTHORIZED BY HONEYWELL, EITHER REMOVE THE AFFECTED ITEM FROM THE ENGINE OR OBTAIN INSTRUCTIONS FOR CONTINUED AIRWORTHINESS FROM THE MANUFACTURER OR THE ORGANiZATION THAT APPROVED THE REPAIR. FAILURE TO USE THIS MANUAL AS DESCRIBED ABOVE MAY ALSO VOID HONEYWELL'S WARRANTY COVERAGE.
290.2
SAFETY WARRANTY/LtABILlTY ADVISORY Page 2 Sept 30/02
HoneyweII MA,NTENAN™UAL LIST OF EFFECTIVE PAGES
CHAPTER/ RFCTinN
PAGE
DATE
Tille Page
-
Sept 30/02
Safety/ Warranty/ Liability Advisory
1 2
Sept 30/02 Sept 30/02
_
Sept 30/02
List o( Effective Pages Record oí Revisions Record oí Temporary Revisions
PAGE
DATE
Sept 30/02 1 2 3 4
Service Bulletin List
Sept 30/02 Sept 30/02 Sept 30/02 Sept 30/02
Sept 30/02
List oí Chapter/ Section/ Subjects
Sept 30/02
INTR0DUCT10N
-
Table oí Contents
-
Introduction
CHAPTER/ RFCTinN
Tab
Sept 30/02 1 2
Sept 30/02 Sept 30/02
290.2
EFF Sept 30/02
HoneyweII
MAINTENANCE MANUAL T53-L-703
RECORD OF REVISIONS REV NO.
ISSUE DATE
DATE INSERTED
BY
REV
ISSUE
NO.
DATE
DATE INSERTED
BY
^
I
290.2 I
REV-REC Sept 30/02
HoneyweII MA,NTENANCE^MANUAL RECORD OF TEMPORARY REVISIONS (CONT)
REV NO.
CHAP/SEC PAGE NO.
DATE ISSUED
DATE INSERTED
BY
DATE REMOVED
BY
tNCORPORATED INTO MANUAL BY REV NO.
1 2
73-20-01 213
Jul 17/91
2
3
72-00-00 605
Auq 28/91
2
72-40-00 219 72-40-00
Oct 29/91
2
5
220
Oct 29/91
2
6
72-40-00 218 72-40-00
Oct 29/91
2
7
232
Oct 29/91
2
8
71-00-00 1
Dec 13/91
2
Feb 19/93
2
4
9
72-00-00 613 80-00-01
10
411 80-00-01
Feb 19/93
2
11
414 80-00-01
Feb 19/93
2
12
416
Feb 19/93
2
13
72-40-04 203
Feb 12/93
2
14
72-51 -00 206
Feb 24/93
2
72-51-00 217 72-40-06
May 24/93
2
16
201
May 24/93
2
17
72-40-06 203
May 24/93
2
15
18
72-51-00 202 71-00-00
Jun 25/93
2
19
9
Jan 31/94
2
290.2-
T-R-REC
Page 1 Sept 30/02
HoneyweII RECORD OF TEMPORARY REVtSIONS (CONT)
REV NO. 20 21 22 23
CHAP/SEC PAGE NO. 71 -00-00 8
DATE ISSUED
DATE INSERTED
BY
DATE REMOVED
BY
INCORPORATED INTO MANUAL BY REV NO.
Jan 31/94
2
Replaced by TR 61 73-20-01 215 Jan 31/94
2
72-40-00 207
Jan 31/94
2
24
72-30-02 216 72-40-00
Feb 1/94
2
25
204 72-00-00
Feb 14/94
2
26
219
Feb 14/94
2
27
72-40-00 215 73-20-01
Nov 20/95
2
June 18/97
2
June 18/97
2
Oct 20/97
2
28 29
210 73-20-01 211 Contents
30 Contents 31
2 Contents
Oct 20/97
2
32
3 Contents
Oct 20/97
2
33
4 Contents 5 Contents
Oct 20/97
2
Oct 20/97
2
6 Contents 7 Contents
Oct 20/97
2
Oct 20/97
2
8 Contents 9
Oct 20/97
2
Oct 20/97
2
34 35 36 37 38
290.2-
T-R-REC
Page 2 Sept 30/02
Honeyi/vell MA,NTENANCE^MANUAL RECORD OF TEMPORARY REV/SIONS (CONT)
REV NO.
CHAP/SEC PAGE NO. Contents
DATE ISSUED
DATE INSERTED
BY
DATE REMOVED
BY
INCORPORATED INTO MANUAL BY REV NO.
39
11 Contents
Oct 20/97
2
40
12 Contents 13 Contents
Oct 20/97
2
Oct 20/97
2
42
14
Oct 20/97
2
43
Contents 16 72-00-00
Oct 20/97
2
Feb 24/00
2
Oct 29/99
2
Oct 29/99
2
Oct 29/99
2
Oct 29/99
2
41
44 45 46 47
619 72-00-00 701 72-00-00 702 72-00-00 703 72-00-00
48
705
49
Reptaced by TR 50 72-00-00
50
211 72-50-03
May 1/00
2
51
201 72-50-03 203
June 19/00
2
June 19/00
2
June 19/00
2
June 19/00
2
June 19/00
2
Oct 20/00
2
Nov 9/00
2
52 53 54 55
72-50-03 204 72-50-03 205 72-50-03 206
o o 1 o o C\I
56
201
o 1 o o ¿ co
57
429
290.2-
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Page 3 Sept 30/02
Honeywell RECORD OF TEMPORARY REVISIONS (CONT)
REV NO.
CHAP/SEC PAGE NO.
DATE ISSUED
DATE tNSERTED
BY
DATE REMOVED
BY
INCORPORATED INTO MANUAL BY REV NO.
58
72-10-01 209
Dec 15/00
2
59
72-30-02 211
Dec 15/00
2
60
80-00-04 413 71-00-00
Dec 15/00
2
61
10
Feb 15/01
2
62
80-00-04 433
Mar 28/01
2
63
72-00-00 623 73-20-01
Apr 5/01
2
64
201
Apr 5/01
2
65
71 -00-00 5
Auq 9/01
2
66
72-00-00 214 72-00-00
Auq 9/01
2
67
215
Aug 9/01
2
68
72-00-00 216
Auq 9/01
2
69
73-20-01 213 73-20-01
July 26/02
2
70
213
Julv 26/02
2
290.2- T-R-REC
Page 4 Sept 30/02
HoneyweII
MAINTENANCE MANUAL T53-L-703
SERVICE BULLETIN LIST NOTE:
SERVICE BULLETIN T53-L-7030001, Rev 13
A date listed in the “Incorp.” column is ihe latest date this report was revised to inelude changes to text/illustrations caused by the Service Bulletin or its revisión When the words "No Effect” are listed, the Service Bulletin caused no changes within this report.
INCORP No Effect
SERVICE RUI i FTiN 0094, Rev 1
INCORP No Effect
0020, Rev 1
No Effect
0096, Rev 1
No Effect
0024
No Effect
0097
No Effect
0029
No Effect
0099, Rev 1
No Effect
0030, Rev 1
No Effect
0100, Rev 2
No Effect
0032
No Effect
0102, Rev 1
No Effect
0036, Rev 1
No Effect
0103, Rev 4
No Effect
0041
No Effect
0104
No Effect
0043. Rev 1
No Effect
0108, Rev 1
No Effect
0049
No Effect
0109
No Effect
0053, Rev 2
No Effect
0110, Rev 1
No Effect
0053
No Effect
0113. Rev 3
No Effect
0054, Rev 1
No Effect
0114
No Effect
0055
No Effect
0115
No Effect
0056, Rev 2
No Effect
0116
No Effect
0057, Rev 1 0058
No Effect No Effect
0117
No Effect No Effect
0060
0119
0061
No Effect No Effect
0120
Sept 30/02 No Effect
0062, Rev 1
No Effect
A0121
No Effect
0063
Sept 30/02
0123
No Effect
0064
No Effect
0124
No Effect
0065, Rev 1
0125
0068
No Effect No Effect
0126
No Effect No Effect
0071
No Effect
0128
No Effect
0078
No Effect
0130
No Effect
0084, Rev 1
No Effect
0131
No Effect
0088, Rev 1 A0092, Rev 1
No Effect No Effect
0132 0133
No Effect No Effect
0093, Rev 2
No Effect
0118
290.2
S-B-LIST Sept 30/02
HoneyweII
MAINTENANCE MANUAL T53-L-703
LIST OF CHAPTER/SECTION/SUBJECTS CHAPTER/ SECTION/ RURJECT SliaiFCT INTRODUCTION STANDARD PRACTICES
70-00-00
POWER PLANT
71-00-00
ENGINE - DESCRIPTION AND OPERATION
72-00-00
REDUCTION GEAR
72-10-00
COMPRESSOR SECTION
72-30-00
COMBUSTION SECTION
72-40-00
TURBINE SECTION GAS PRODUCER SYSTEM COMPONENTS
72-50-00 72-51-00
ACCESSORY ORIVE SECTION
72-60-00
ENGINE FUEL & CONTROL
73-00-00
IGNITION
74 - 00 - 00
AIR
75-00-00
ENGINE CONTROLS
76-00-00
ENGINE INDICATING
77-00-00
OIL
79-00-00
HEAVY MAINTENANCE
80-00-00
290.2
CHAPTER/SECTION/SUBJECT S Sept 30/02
HoneyweII INTRODUCTION TABLE OF CONTENTS
SUBJECT
CHAPTER/ SECTION/ SUBJECT
INTRODUCTION General Logbook Use Notes, Cautions, and Warnings Supplementary Publications for T53-L-703 Gas Turbine Engines Parts and Service
PAGE
1 1 1 2 2
290.2
CONTENTS Sept 30/02
HoneyweII
MAINTENANCE MANUAL T53-L-703
INTRODUCTION 1.
General A.
This publication provides mamtenance instructions for support of T53-L-703 engines manutactured by HoneyweII Engines, Systems & Services. Phoenix, AZ.
B.
This manual, as it may be supplemented by HoneyweII Engines, Systems & Services Service Bulletins, constitutes the authoritative statement of HoneyweII Engines, Systems & Services’ approved and recommended maintenance procedures.
C.
Unusual problems concermng engine maintenance should be presented to the Customer Support Department either through its field Service representativas or by direct contact. All possible assistance will be provided toward solution of these problems.
D- Requests for Information not presently covered by this publication and suggestions for modification or amplification of these instructions so as to increase their usefulness are weicomed by the HoneyweII Engines, Systems & Services Military Customer Support Center. inquires of a technical nature regarding this publication should be directed to; Military Customer Support HoneyweII Engines, Systems 8> Services 111 South 34th Street RO. Box 52181 Phoenix, Arizona 85072-2181 Attention: Manager, Customer Support Engineering E.
2.
HoneyweII Engines, Systems & Services has a continumg program to develop retine assemblyinspection and test techniques, etc, which will be issued as regular revisions to the manual. Data of a more urgent nature is supplied by Temporary Revisions and keyed to the appropriate sections of the manual. Significant engine modifications are covered by issuance of Service Bulletins.
Loqbook Use A logbook is packaged with each engine and is issued to provide a document for recording maintenance actions, operating time, and cycles, and to provide immediate summary of operating history. Instructions for using the logbooks are located on the first page.
3.
Notes. Cautions and Warninos A.
Notes, cautions and warnings are found throughout the manual. Notes, cautions and warnings precede the text to which each applies. Conditions for use are as follows; WARNING: TO HIGHLIGHT PROCEDURES, ETC, WHICH SHOULD RESULT IN PERSONAL INJURY OR LOSS OF LIFE, iF NOT CORRECTLY FOLLOWED. CAtJTION:
NOTE:
TO HIGHLIGHT PROCEDURES. PRACTICES, ETC, WHICH IF NOT STRICTLY OBSERVED, WILL RESULT IN DAMAGE TO OR DESTRUCTION OF EQUIPMENT.
To highiight essential procedure, conditions, Information, etc.
290.2- INTRO
Page 1 Sept 30/02
HoneyweII 4.
MAINTENANCE MANUAL T53-L-703
Supplementary Publications for T53-L-7Q3 Gas Turbine Engines A.
Engine Overhaul Manual Report No. 290.3
B.
Illustrated Parts Catalog Report No. 290.4
C.
Engine Repair Manual Report No. 72-09-30
D.
Standard Practices Manual Report No. 286.2
E.
Sen/ice Bultetin Service Bulletins are issued as required to provide Information or instructlons for special inspections or modifying engines or parts. Service Bulletins appiicable to the engine modeis covered by this manual are reflected in the List of Service Bulletins in the front of this manual.
F.
Publications Index The Publications Index is issued quarterly to provide a status list which operators can use to evalúate all technical support data (i.e. manuals, catalogs, Service letters, Service bulletins, etc).
G.
Service Letters Service Letters are issued as required to advise operators of changes to maintenance procedures or to highiight Information which will enhance engine maintenance or operation.
5.
Parts and Service Refer to Illustrated Parts Catalog, Report No. 290.4, Introduction for Information on ordering of parts.
290.2- INTRO
Page 2 Sept 30/02
HoneyweII
MAINTENANCE MANUAL
T53-L-703 ^^TANDARD PRACTICES TABLE OF CONTENTS
RLJBJECT STANDARD PRACTICES Deleted
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MAINTENANCE MANUAL T53-L-703
STANDARD PRACTICFS I Standard Practices section has been deleted. Refer to Standard Practicas Manual, Report No. 286.2
70-
00-00
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HoneyweII POWER PLANT TABLE OF CONTENTS
SUBJECT POWER PU\NT General Fuel Requirements Lubricating Oil Requirements Engine Inspection Before Operation Prestar! Checks Engine Motoring Fuel Control Priming Engine Starting Engine Pires Operating Limits Engine Operation Checks Extreme Weather Operation
CHAPTER/ SECTION/ SUBJECT
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LIST OF EFFECTIVE PAGES
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71- EFF Sept 30/02
Honeyi/vell
MAINTENANCE MANUAL T53-L-703
POWER PLANT 1.
General This chapter contains instructions for normal ground operation of engine installed In aircratt to determine flight readiness. AIso Included are fuel data, oil data, preoperational engine inspection requirements, engine operation and limits data, operational checks and e)ftreme weather precautions.
2.
Fuel Requirements A.
Specitied Fueis WARNING: WHEN USING KEROSENE FUELS {JP-5 OR JP-8). RESTARTING ENGINE DURING FLIGHT IS POSSIBLE UP TO AN ALTITUDE OF 8000 FEET MAXIMUM. USE OF THESE FUELS SHOULD BE AVOIDED WHEN STARTINGATAMBIENT TEMPERATURES BELOW 10’F (-12’C). NOTE:
There are no special restrictions or instructions for use of JP-4 fuels. with the exception of restarting engine during flight being hmited to altitudes up to 15,000 feet máximum.
The fuels specified for use in these engines conform to Military Specification MIL- DTL-5624 and are either wide-cut type fuels. Grade JP-4, or kerosene type fuels. Grade JP-5. Equivalent fuels, MILDTL-83133. Grade JP-8, may be used. (See paragraph B.) B.
Acceptable Wide Cut and Kerosene Type Engine Fuels and Freezing Points (1)
All engine fuels Usted are fully approved for flight operation. In cases where fuels approved by HoneyweII are not available and other fuels musí be substituted, consult with: Military Customer Support HoneyweII Engines, Systems & Services 111 South 34th Street RO. Box 52181 Phoenix, Arizona 85072-2181 Attention; Manager. Customer Support Engineering
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HoneyweII NOTE:
(2)
Variations in wide cut fuei quality or the use of kerosene type fueis can increase the rale of carbón deposif on hot end parts, especially during long periods of steady State operation. Accumulation of deposits can be minimized by changing power leveis periodically during operation.
Wide cut type equivalen! fuels. The following wide cut fueis may be used. (a)
Commercial wide cut type fuels, freezing point -56°F (-49°C). CAUTION:
COMMERCIAL FUELS ARE COMMONLY MADE TO CONFORM TO AMERICAN SOCIETY FOR TESTING AND MATERIALS (ASTM) SPECIFICATION D 1655. ASTM SPECIFICATION FUEL DOES NOT CONTAIN ANTI-ICING ADDITIVES UNLESS SPECIFIED BY BULK PURCHASER. THEREFORE, MORE CARE THAN USUAL MUST BE TAKEN WITH RESPECT TO WATER CONTAMINATION AND FLIGHT CONDITIONS WHEN ACCEPTING SUCH A FUEL D 1655 TypeA ASTM Specification American JP-4 American Arcojet B Arco B. P Trading BP A.TG. Cal-Tex Caltex Jet B Chevron Chevron B Continental Conoco JP-4 Exxon Exxon Turbo Fuel B Gulf Gulf Jet B Mobil Mobil Jet B Philhps Philjet JP-4 Shell Aeroshell JP-4 Texaco Texaco JP-4 Union Union JP-4
(b) Military wide cut type fuels, freezing point -72°F (-58°C). NATO Belgium Britain Cañada Denmark Federal Republic of Germany France Greece Italy Netherlands Norway Portugal Turkey United Kingdom United States
F-40 BA-PF-2B D. Eng. R.D. 2486 3-GP-22f MIL-DTL-5624, GR JP-4 VTL 9130-006 AIR 3407/A MIL-DTL-5624, GRJP-4 AA-M-C-1421 MIL-DTL-6624, GR JP-4 MIL-DTL-5624, GR JP-4 MIL-DTL-5624, GR JP-4 MlL-DTL-5624, GR JP-4 D. Eng. R.D. 2454 MIL-DTL-5624, GR JP-4
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HoneyweII (3)
Kerosene type equivalen! fuels. The following kerosene type fueis may be used. (a)
Commercial kerosene type fuels, freezing point (-38’C). CALJTinN: COMMERCIAL FUELS ARE COMMONLY MADE TO CONFORM TO AMERICAN SOCIETY FOR TESTING AND MATERIALS (ASTM) SPECIFICATION D 1655. ASTM SPECIFICATION FUEL DOES NOT CONTAIN ANTI-ICING ADDITtVES UNLESS SPECIFIED BY BULK PURCHASER. THEREFORE, MORE CARE THAN USUAL MUST BE TAKEN WITH RESPECT TO WATER CONTAMINATION AND FLIGHT CONDITIONS WHEN ACCEPTING SUCH A FUEL. ASTM Specification D1655 Type A American American Jet Fuel Type A Arco Arcojet A British American B-AJet Fuel JP-4 Chevron Chevron A-50 Cities Service Citgo A Continental Conoco Jet 50 Exxon Exxon A Gulf Gulf Jet A Mobil Mobil Jet A Phillips Philjet A-50 Puré Purejet Turbine Fuel Type A Shell Aeroshell Turbine Fuel 640 Standard Jet A Kerosene Texaco Texaco Avjet A Union 76 Turbine Fuel Commercial kerosene type fuels, freezing point -55°F (-48°C). ASTM Specification Arco BP Trading Cal-Tex Chevron Continental Exxon Gulf Mobil Puré Shell Sinclair Standard Texaco Union
D-1655Type A-1 Arcojet A-1 BP A.T.K. Caltex Jet A-1 Chevron A-1 Conoco Jet-60 Exxon A-1 Gulf JetA-1 Mobil JetA-1 Purejet Turbine Fuel Type A Aeroshell Turbine Fuel 650 Super Jet A-1 JetA-1 Kerosene Avjet A-1 76 Turbine Fuel
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HoneyweII (c)
Military kerosene type fueis, freezing point -40°F (-40’C). NATO France
(d)
F-42 Air 3404
Military kerosene type fueis, freezing point -58°F (-50“C). NATO Denmark France United Kingdom NATO Federal Republic of Germany United Kingdom
{e>
Military kerosene type fuels, freezing point -51 °F {-46°C). NATO Australia Belgium Ganada Federal Republic of Germany Italy Netherlands United Kingdom United States
C.
F-34 D. Eng. R.D. 2453 Air 3405/B D. Eng. R.D. 2453 F-35 D. Eng. R.D. 2494 D. Eng. R.D. 2494 F-44 DEF 207 BA-PF-6 3-GP-24 D. Eng. R.D. 2452 AER-M-C-143 D. Eng. R.D. 2498 D. Eng. R.D. 2498 MIL-DTL-5624, GR JP-5
Additives (1)
The following additives, singly or in any combination, additional to those included in the fuel specification, are approved subject to limitation stated. NOTE:
(2)
The following additives should not be added to fuel MIL-DTL-5624, Grades JP-4, JP-5, or MIL-DTL-83133 JP-8 since they are already present in these fuels.
Antl-corrosion additive {DERD2461 and APL2461). Additive may be added in quantities not exceeding 4.0 pound per 1000 barréis and phosphorus contení of 0.006 parts per million. CAUTIQN:
NOTE:
ANTI-ICING ADDITIVE IS REQUIRED AT AMBIENT TEMPERATURE OF32'‘F(0°C).
Biocidal additive (methyl cellosolve) should not be added in combination with anti-icing additive.
(3)
Anti-icing and biocidal additives (D. Eng. R.D. 2451). Additive {MIL-l-27696 or any direct equivalent) may be added in concentrations not exceeding 0.15 percent by volume.
(4)
Biocidal additive (methyl cellosolve). Additive may be added to fuel in concentrations of 0.15 to 0.25 percent by volume. The lower concentrations being used on a continuous usage or intermittent basis to prevent contamination and the higher concentrations are intended to be used for shock treatment.
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HoneyweII CAUTIQN:
3.
MAKE SURE THAT BIOBOR JF IS THE ONLY BIOBOR PRODUCT USED.
(5)
Biocidal additive (Biobor JF). Additive may be used for shock treatment at a concentration not exceeding 270 parts per million (ppm) (20 ppm Boron) or preventive treatment at a concentration of 135 ppm (10 ppm Boron).
(6)
Anti-static additive (Shell or Royal lubricants A.S.A,3). Additive may be added to fuel in concentrations as required to bring conductivity within 200 to 600 pico Siemens per meter at point and time of deiivery into the aircraft as measured with a conductivity meter.
Lubricatino Oil Reguirements CAUTIQN:
A.
INTERMIXING OF OILS OF DIFFERENT BRANDS SHOULD BE AVOIDED IF POSSIBLE. INTERMIXING OF OILS OF DIFFERENT TYPES IS NOT PERMITTED EXCEPT IN AN EMERGENCY. IF INTERMIXING OF OIL TYPES BECOMES NECESSARY. THE OIL SYSTEM MUST BE FLUSHED WITHIN 6 HOURS OF ENGINE OPERATION. (SEE 72-00-00, ENGINE SERVICING.)
The Engine Lubrication System Oiis Specified for Use in These Engines Conform To Or Are Similar to Military Specifications MIL-PRF-7808 or MIL-PRF-23699 The oiIs listed in the following paragraphs are approved for engine fhght operation (1)
The following oiis areType ((MIL-PRF-7808) and are satisfactory for engine starting at ambient temperaturas down to -65°F (-54°C). BP Turbo Oil 2369 Brayco 880H Exxon 2389 Mobil Jet 184A/201A Royco 808GF Stauffer Jet l
(2)
The following oils are Type II (MIL-PRF-23699) and are satisfactory for engine starting at ambient temperaturas down to -40°F (-40°C). BP Turbo Oil 2380 Castrol 205 Exxon 2380 Mobil Jet Oil I! Shell 500 Stauffer Jet II
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HoneyweII NOTE:
MAINTENANCE MANUAL T53-L-703
When oiis approved by HoneyweII Engmes, Systems & Services are not available and other oiis must be substituted, consult with: Military Customer Support HoneyweII Engines. Systems S Services 111 South 34th Street PO. Box 52181 Phoenix. Arizona 85072-2181 Attention: Manager, Customer Support Engineenng
4.
Engine Inspection Before Operation See 72-00-00, Engine - Inspection, paragraph I.A.
5.
Prestan Checks Perlorm Prestad CheCks In Accordance With Instructions in Aircraft Manual
6.
Engine Moloring NOTE:
This procedure is not necessary for normal starting.
A. Motor Engine During Fue! Control Unit Priming or Other Operations (1)
Disconnect electrical power input from ignition unit.
(2)
Check that throttie is in OFF position. CAUTIQN:
(3) 7.
TO PREVENT DAMAGE TO STARTER, DO NOT EXCEED STARTER LIMITATIONS.
Motor engíne with starter.
Fuel Control Priming NOTE:
This procedure is not necessary for normal starting.
Prime Fuel Control Assembly (See 72-00-00, Engine - Servicing, paragraph 3.) 8.
Engine Starting and Operation Engine Shall Be Started and Operated tn Accordance With Instructions in the Aircraft Manual
9.
Engine Fires A. Engine onFire (1)
Cióse throttie (N,).
(2)
Cióse main fuel vaive.
(3)
Motor engine until fire Is extinguished.
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HoneyweII -^EMANUAL WARNING: AVOID INHALATION OF CB FUMES. IF CB CONTACTS SKIN OR EYES, IMMEDIATELY FLUSH WITH RUNNING WATER; THEN WASH THOROUGHLY W!TH SOAP AND WATER. CAUTION:
NOTE:
IF CO2 AGENT WAS APPLIED TO ENGINE AIR INLET WITH ENGINE ROTATING, A HOT END INSPECTION MUST BE PERFORMED. BROMOCHLOROMETHANE (CB) IS A TOXIC, CORROSIVE AGENT. DILUTION WITH WATER INCREASES ITS CORROSIVE EFFECT If burning ON in the tailpipe is minor and presenta no danger to aircraft, it is permissible to allow flames to consume all residual fuel without using fire METALS. extinguisher. Danger to aircraft is greater than danger to interna! parts of engine. If fire extinguishing agent Bromochioromethane (CB) was used, immediately purge exposed engine and aircraft surfaces with deán, dry air and wash with dry cleaning solvent (72-00-00, 62, Table 203). Clean engine compressor using dry cleaning solvent method. (Refer to SPM, 70-15-03. SP C203.) If fire extinguishing agent other than CO2 or Bromochioromethane (CB) was used, remove residue from engine by washing exterior and cleaning compressor using water wash procedure.
(4)
If fire persiste, extinguish it with suitable fire extinguisher applied to engine air inlet if engine is still rotating or directly to base of flames if rotation has stopped.
10. Qoerating Limits (See Table 1 and Figure 1) A.
Deleted
B.
Engine Overíorque Limits Output shaft torque shall not exceed following valúes: NOTE: If limits are exceeded, an engine overtorque inspection must be performed. (See 72-00-00, Engine - Inspection, paragraph 1.F.(6}-) (1)
Military (30 minutes) 1175 foot pounds (64 psi).
(2)
Máximum continuous 1110 foot pounds (60 psi).
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MAINTENANCE MANUAL
■ ■OílCywwdl
T53-L-703
Table 1. Engine Steady State Operating Limits Under AH Ambient Conditions
Mechanical Power Rating
Max. Compressor Rotor Speed (Ni) (Percent)
Max. Power Turbine Speed (N2) (RPM)
Military (30 Minutes)
105.8
21,300 (101%)
Normal (Continuous)
101
21,300 (101%)
NOTE: 100% Ni 100% N2 = =
C.
Max. Shaft Horsepower (SHP)
Max. Torque Indicated (PSI)
Max. Inlet Oil Temp
64
200“F (93°C)
80 tolOO
1485
60
200''F (93°C)
80 to 100
1350
25,150 RPM 6,564 Output Shaft RPM 21,075 Turbine RPM
Overtemperature Limits NOTE: (1)
If limtt is exceeded, an internal (hot end) inspection must be performed. (See 72-00-00, Engine - Inspection, paragraph I.D.)
An overtemperature condition exists. During starts or accelerations when MGT exceeds 1742°F (950°C). NOTE:
D.
Max. Turbine Gas Temp 1616’F (880 °C) 1508’F (820 °C)
Oil Pressure Limits NRP and Above (PSIG)
It the engine cannot be operated without exceeding military power or máximum continuous rated power MGT limits, this is an indication of operation in excess of normal capabilities, engine malfunctlon or instrument error.
(2)
An overtemperature condition exists. At military power when MGT exceeds 1616°F {880°C).
(3)
An overtemperature condition exists. At máximum continuous rated power when MGT exceeds 1508°F (820'’C).
Overspeed Limits An engine overspeed exists under the following conditions; (1) (2)
When Ni speed exceeds 105.8 percent (26,600 rpm} at any time. In transient Ns speed Table 1 limits maybe exceeded to 109 percent (23,000 power turbine rpm for a máximum of two seconds, output shaft - 7163 rpm) at any power lever position.
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MAINTENANCE MANUAL T53-L-703
COMPENSATED SHAFT HORSEPOWER - SHP/A
HoneyweII
Compensated Shaft Hofsepower Versus Ambient Temperature Figure 1
71- 00-00 SeSo2
HoneyweII — E- Olí Overtemperature Limits An engme oil overtemperature condition exists when the following limits are exceeOed: (1)
Oil temperature limits for normal operating conditions: (a)
The máximum (red line) OIL IN temperature is 210^ (99°C).
(b)
A steady State engine OIL IN temperature of 212°F (100°C) is acceptable provided an oil overtemperature inspection is performed. (See 72-00-00, Engine - Inspection, paragraph 1.R(7)-)
CAUTION:
(2)
F.
IT MUST BE CLEARLY UNDERSTOOD THAT THERE IS A POSSIBILITY THAT MECHANICAL COMPONENTS MAY SUFFER DAMAGE IF ENGINE OPERATING CONDITIONS ARE EXTENDED BEYOND THESE RECOMMENDED LIMITS.
Oil temperatures exceed the above limits, the following procedures apply. (a)
Oil temperature of 201 to 266°F (94 to 130°C) for 10 minutes or less is acceptable provided an oil overtemperature inspection is performed. (See 72-00-00, Engine - Inspection, paragraph 1 .F.(7).)
(b)
Oil temperature of 201 to 266°F (94 to 130°C) for more than 10 minutes, but no more than 30 minutes, is acceptable provided an oil overtemperature inspection is performed. (See 72-00-00, Engine - Inspection, paragraph 1.F.(7).)
(c)
When oil temperature has reached 268 to 300°F (131 to 149°C) for any time period, perform an oil overtemperature inspection. (See 72-00-00, Engine - inspection, paragraph 1. F.(7).)
(d)
When oil temperature has reached 302°F (150°C) or above. engine must be returned to Overhaul.
Engine G-Loading NOTE:
If it is suspected that limits have been exceeded, an excessive G-load inspection must be performed after flight concerned. (See 72-00-00, Engine - Inspection, paragraph 1.F.(8).)
The máximum G-loads of the specified forces are as follows: Vertical Side Forward Aft
10G 4G 3G 4G
n. Engine Qoeration Checks A.
Check Run After Initial Installation or Repair/Replacement of Major Components (1)
Perform vibration check as requtred. (See paragraph 10.E.)
(2)
Start engine (paragraph 8) and stabilize at flight idie.
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HoneyweII
B.
(3)
Check for 70 to 72 percent N1 speed. Check for oil pressure indication. Shut down engine and if required, adjust idie rpm. (See 73-20-01. Fuei Control - Adjustment/TesL)
(4)
Check operation of hot air solenoid valve. (See 75-10-02.)
(5)
Perform power check and trim adjustment. (See 73-20-01.)
(6)
Check operation of emergency (manual) fuel System. (See paragraph 10.D.)
(7)
Shut down engine. (See paragraph 10.F.)
Initial Check Run (1)
Remove the main oil filter cover assembiy. Clean the cover assembly in dry cleanmg solvent (72-00-00, 62, Table 203) and reinstall. NOTE:
C.
MAINTENANCE MANUAL T53-L-703
tt is not advisable to mix M1L-PRF-23699 type oil with MlL-PRF-7808 type oil except in case of emergency. tf this becomes necessary, it is required that the system be flushed within 6 hours.
(2)
Pili aircraft 0(1 tank wtth 0(1.
(3)
Start engine. (See paragraph 8.)
(4)
Opérate engine for several minutes at flight idie and then shut down.
(5)
Inspect engine for leaks and security of mounting of hoses and accessories.
(6)
Start engine and run at flight idie for 3 minutes, accelerate gradually until highest power, without gaining flight attitude, is obtained and temperatures have stabilized.
(7)
Decelérate engine to flight idie and run for 2 minutes to allow MGT to stabilize, shut down engine. Inspect engine. (See paragraph 10.0.)
Inspection After Initial Check Run (1)
Inspect engine for leaks and security of mounting provisions, hoses and accessories.
(2)
Inspect engine main oil filter and chip detector for accumulation of metal chips, lint or other foreign material in oil filter.
(3)
If there is no accumulation of metal chips, lint or other foreign material, continué with engine operation checks.
(4)
If there is a slight accumulation of metal chips, lint or other foreign material, clean and reinstall the chJp detector and oil filter, Restart engine and perform a second run for several minutes at highest power obtainable without gairiing flight attitude. If further accumulation is found, proceed to step (5).
(5)
If there is an excessive accumulation of metal chips, lint, or other foreign material, further in\/est/gation is required. (See 72-00 -00, Engine - Trouble Shooting, paragraph 1 .C.)
(6)
Remove, inspect, clean and reinstall fuel control filters.
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MAINTENANCE MANUAL
noncyi/vdi NOTE:
D.
T53-L-703
After installing an engine or a fuel control dunng the sen/ice inspection or when a special verification of the proper operation o< the luel control emergency (manual) system is required, perform the tollowing check.
Operational Check of Emergency (Manual) Fuel System (1)
Start engine. (See paragraph 8.) CAUTIQN:
(2)
With the fuel control selector switch in the AUTO position, stabilize engine at 70 to 72 percent NI speed.
(3)
Move the fuel control selector switch to the EMER position. NOTE:
E.
SELECT MAXIMUM Ng SPEED WITH THE GOV RPM INCR-DECR BEEP SWITCH BEFORE STABILIZING ENGINE AI 70 TO 72 PERCENTNi SPEED,
Ni speed in EMER position is governed directly by throttie position and may change 2 to 5 percent mínimum.
(4)
Note Ni speed, it should drop 2 to 5 percent mínimum.
(5)
Return fuel selector to AUTO position within 5 seconds of moving to EMER position.
(6)
The regulator should respond with a rise in Ni speed.
Engine Vibratíon Test An engine vibratíon test is required after initia! installation of engine to aircraft, after combustor turbine assembly (hot end) is removed and reinstalied, after repair of certain engine components, after removal or adjustment of any engine mounts. mount shims, mount bearings, when excessive engine vibration is suspected and to complete a dropped engine inspection. An inspection vibration test, using vibratíon check tool kit LTCT14664-02 or LTCT28430-01, measures vibration at specified NI and N2 operating speeds. Vibration pickups, attached to adapters mounted on engine. transmit electrical impulses through cables to a vibration meter. The vibration meter indicates total amount of engine movement (peak to peak displacement) in mils. (See Figures 2 and 3.) Meter indications are recordad on an Engine Vibration Test Data Sheet. The recorded figures are compared with figures given on data sheet for máximum permissible engine vibration. If these máximum figures are exceeded, the cause of the excessive vibration must be found and corrected before engine can be accepted for unrestncted flight.
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HoneyweII
MAINTENANCE MANUAL T53-L-703
Vibration Meter Figure 2
NOTE:
Acceplable atternative vibration measurement equipment inciudes the Chadwtck Helmuth (CH) 192 analyzer with the 7460A high low filter using the CEC 4-118-0107 or 4-128-0101 pickups for normal vibration checks. Follow CH operating instructions and engine vibration limite and testing parameters.
(1) Vibration test preparations. Each of the following procedural steps, including checks and adjustments of vibration equipment, must be repeated each time equipment is assembled for ar engine vibration test. AH equipment required, with the exception of mount assembly LTCT6756, IS included in vibration check tool kit LTCTt4664-07. Thís set contains a vibration meter LTCT23844-01. Proceed with following vibration test using applicable procedures in accordance with the specific vibration meter being used. (a)
Deleted
(b)
Deleted
(c)
Deleted
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R£4R VIEW
Vibration Meter Figure 3
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HoneyweII
(2)
(3)
(4)
MAINTENANCE MANUAL T53-L-703
(d)
Deleled.
(e)
Operationai check of vibration pickups. (See step (6).)
(f)
Installation of vibration equipment. {See step (7).)
(g)
Adjustment of vibration meter. (See step (8) or (9).)
(h)
Vibration test- (See step (10).)
(i)
Deleted.
(j)
Evaluationof vibration test data. (See step (12).)
(k)
Correcting vibration. (See step (13).).
If it is not certam that proper filters are at the proper locations, they must be installed as follows: (a)
Remove meter housing.
(b)
Plug 70 Hz high pass filter CEC1 -003-0070 into INPUT NETWORK Socket No. 1.
(c)
Plug 200 Hz high pass filter CEC1 -003-0200 into INPUT NETWORK Socket No. 2.
(d)
Secure filters with screws provided.
(e)
Instan meter housing.
Filter inspection LTCT14664-07. Vibration meter LTCT22031-01 has filters (LTCT20596-01) installed. Install filters LTCT14664-07 in vibration meter LTCT23844 - 01 as follows: (a)
Remove meter housing.
(b)
Plug 70 Hz high pass filter LTCT23842-01 or CEC1 -003-0070 into filter Socket No. 2.
(c) (d)
Plug 200 Hz high pass filter LTCT23843-01 or CECI -003-0200 into filter Socket No. 3. Secure filters with screws provided.
(e)
Instan meter housing.
Deleted. WARNING: DELETED. (a)
Deleted.
(b)
Deleted.
71- 00-00
Page 15 Sept 30/02
HoneyweII >^A,NTENANCEMANUAL (5)
Preliminat7 warmup. WARNING: TO PREVEN! A POSSIBLE HAZARD JO PERSONNEL AND DAMAGE TO EQUIPMENT, SET POWER SWITCH TO OFF WHILE CONNECTING TO A POWER SOURCE. NOTE:
(a)
Connect power lead to suitable source of electncal power (105 to 125 volts, 50/60/400 Hertz) or use 18 vdc battery power suppiy.
(b)
With power switch on, allow approximately 10 minutes for temperatura to stabilize within the meter.
CAUTION:
(6)
With AC power, use connector adapter LTCT9280, supplied with kit, if necessary.
HANDLE VIBRATiON PICKUPS WITH CARE. IFAPlCKUPIS DROPPED OR STRUCK WITH FORCE. ITS ACCURACY MAY BE IMPAIRED.
Operational check of vibration pickups as follows: CAUTION:
DO NOT INTERMIX PICKUPS. USE EITHER THREE EACH CEC4-118-0107, LTCT9282. OR THREE CEC4-128-0101 PICKUPS. SENSITIVITY SETTINGS DIFFER WITH EACH TYPE AND THEREFORE, CANNOT BE INTERMIXED.
(a)
While meter is warming up. lay out three cable assemblies CEC49657-0300 or LTCT9283-02 and three vibration pickups CEC4-118-0107, LTCT9282 or CEC4-128-0101.
(b)
Connect cables to pickups and to proper CHANNEL receptacle in vibration meter.
(c)
Apply to meter LTCT9281 as follows: 1
Set INPUT NETWORK selectors to OUT.
2
Set OPERATION selector to Dxl. 0.
3
Set CHANNEL selector to 1.
4
Set RANGE selector to 5. NOTE: If indicator does not move, check condition of pickup, connectors, cable, and vibration meter receptacle. Interchange components until detective unit is found. Replace detective component.
5
Slowly move No. 1 pickup by hand, while obsen/ing vibration meter. Indicator should jog or show a slight movement.
£ Set CHANNEL selector to 2, then to 3 and using same procedures. check operation ot remaining pickups.
71- 00-00
Page 16 Sept 30/02
HoneyweII ‘--NTENANCBMA.UAL (d)
Apply to meter LTCT22031-01 or LTCT23844-01 asfollows: NOTE:
Vibration meter contains an infernal plug in power supply (AC). AC power supply may be wired for high or low voltage by changing transformer strapping from 115 V range to 230 V range. A battery (18 DC) power supply is aiso included in LTCT20596-01 or LTCT14664-07.
1
Connect vibration meter to power source to be used. (If batteries are not to be used.)
2
Make sure connector plug at rear of vibratron meter chassis is inserted into external tilter receptacle.
3
Set SELECTOR switch to OUT position.
4
Depress CHANNEL selector 1.
5
Set MODE switch (inner parí of RANGE switch) to D (disp)acement) posilion.
6 7
Set RANGE switch to 5. Slowly move No. 1 pickup by hand while observmg meter indication. (ndicator should jog or show slight movement. NOTE:
!f the indicator does not move, check position of pickup, connectors, cable and meter receptacle. Interchange components until detective unit is found. Replace detective component.
S Repeat steps 1 through 7 for the remaining CHANNELS 2 and 3 in use. (7)
Installation of vibration equipment as follows: NOTE:
In following step (a), cable and pickup to CHANNEL 1 will connect to front lifting eye adapter. Cable and pickup to CHANNEL 2 will connect to diffuser ílange adapter. Cable and pickup to CHANNEL 3 will connect to oil scavenge line adapter or to No. 3 and 4 bearing vibration pickup mount assembly LTCT6756, used as an altérnate to oiJ scavenge line adapter on cerlain aircraft applications.
(a)
Secure pickup mounting adapters to required engine mounting locations. (See Figure 4.)
(b)
Secure each pickup to its adapter with three 4-40 screws and suitable lockwashers.
71- 00-00
Page 17 Sept 30/02
HoneyweII
K 7« «2C
Location of Vibration Pickup Adapters Figure 4
71 00-00 -
Page 18 Sept 30/02
HoneyweII CAUTIQN:
NOTE:
LEAVE ENOUGH SIJ\CK IN CABLE TO PREVEN! UNNECESSARY STRAIN ON PICKUPS AND CONNECTORS. AVOID CONDITIONS THAT WOULD CAUSE CABLES TO DETERIORATE FROM HEAT OR ABRASION.
Identify adapter and cable connections with numbers or colors to make certain that pickups will be connected to proper meter CHANNEL receptacles.
(c)
Connecí proper cable to each pickup.
(d)
Secure cable assemblies to engine and aircraft with tape or cord. WARNING: TO PREVEN! A POSSIBLE HAZARD TO PERSONNEL AND DAMAGE TO EQUIPMENT. SET METER POWER SWITCH TO OFF, WHILE BREAKING OR MAKING CONNECTION TO A SOURCE OF ELECTRICAL POWER. NOTE:
(8)
To prevent cooling off of vibration meter, it must not be without a source of power for more than a few minutes.
(e)
Disconnect meter from source of power used for preliminary warmup and immediately connect it to aircraft electrical power (105 to 125 volts, 50/60/400 Hertz, 30 watts).
(f)
Secure vibration meter with bungee cord (shock cord) or other suitable means, to a cushioned, protected location in aircraft cabin.
(g)
Connect cable assemblies to proper CHANNEL receptacles.
Adjustment of vibration meter LTCT9281 asfollows: NOTE:
With OPERATION selector set at C, the INPUT NETWORK selector and RANGE selector may be in any position.
(a)
Set OPERATION selector to C. tndicator should swing toward right hand side of scale.
(b)
Set CHANNEL selector to 1.
(c)
Push in CALIBRATE SIGNAL control. Turn until indication is 10.5 for the CEC4-118-0107 (LTCT9282) or 6.0 for the CEC4-128-0101 pickups. Read on the 0 to 15 scale.
(d)
Release CALIBRATE SIGNAL control carefully without turning.
(e)
Open panel below CALIBRATE SIGNAL control to expose SENSITIVITY Controls.
(f)
Turn SENSITIVITY control for CHANNEL 1 to obtain analyzer indication of 15.0.
71 00-00 -
Page 19 Sepí 30/02
HoneyweII NOTE: (g)
Confirm proper adjustment of CHANNEL 1 by pushing in and releasing CALIBRATE SIGNAL control, while obseiving for consistent Indications of 10.5 (CEC4-118-0107) or 6.0 (CEC4-128-0101) and 15.0. NOTE:
(h)
Oniy one setting of 10.5 (or 6.0) made at CHANNEL 1 is necessary for use with all channels.
Obtain indication of 15.0 for remaining channels by setting CHANNEL selector to proper number and turning SENSITIVITY control for that channel.
CAUTION:
NOTE:
(9)
It an indication of 10.5 or 15 0 cannot be oblained, vibration anaiyzer must be recalibrated internally by quaiified personnel.
TO MAKE SURE ACCURACY OF VIBRATION TEST. ADJUST VIBRAT10N METER USING SAME POWER SOURCE THAT IS TO BE USED DURING VIBRATION TEST.
If using battery power suppiy. set SELECTOR switch in OFF position. Battery voltage is sufficient when meter reading on 0 to 5 scale is one vo¡t or greater. Set SELECTOR switch in íhe BATT posilion. Again, battery voltage must be one volt or greater.
Adjustment of vibration meter LTCT22031 -Oí or LTCT23844-01 as follows: (a)
Connect power source to be used (if batteries are not to be used).
(b)
Check continuity of transducer circuits by placing RANGE switch to 500, setting SELECTOR switch to CONT position and depressing selected channels on CHANNEL SELECTOR. If Circuit is satisfactory, meter will read within the green 2one. If channel is open, indicator will deflect full scale. When Circuit is shorted, indication will be ZERO.
(c)
Place SELECTOR switch to CALIB and adjust OSC LEVEL for full scale meter deflection.
(d)
Place SELECTOR switch to SENS ADJ. NOTE:
It is necessary to adjust the SENSITIVITY control on CHANNEL 1 oniy, to the correct setting for type of pickups in use. This will suffice for remainder of channels in use. However, CHANNEL GAIN, located above the CHANNEL SELECTOR buttons, must be individually adjusted for each channel in úsele) Depress CHANNEL SELECTOR 1 and set the SENSITIVITY control to correct transducer sensitivity for type of pickup in use. Either 10.5 or 6.0 for CEC4-118-0107 or CEC4-128-0101 pickups, respectively. Set 10 or 6 into window of control and 5 or 0 on the inside vernier. (f)
Adjust channel gain potentiometer (smailest set screw immediately ahove the CHANNEL SELECTOR) for CHANNEL 1 to obtain a full scale deflection indication.
(g)
Repeat above step (e) for remaining CHANNELS 2 and 3.
71 00-00 -
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HoneyweII MA,NTENANCEMAN.AL NOTE:
(10)
Check aircraft engine mounts for looseness, wear, or insutficient torque before attempting vibration test. Ensure that Marman clamps, inlet screens, exhaust pipe and a)) damps, ¡ines and hoses are secura
Vibration test as follows; (a)
Prepare Engine Vibration Test Data Sheet for engine to be tested by suppiying applicable information at top of data sheet. (See Figure 5.)
(b)
Following steps (c) through (g) apply to vibration meter LTCT22031-01 or LTCT23844 -01.
(c)
If not using batteries, make sure that vibration meter power source is on.
(d)
Set SELECTOR switch to proper number for filter to be used as required by data sheet.
(e)
Set MODE switch to D position.
(f)
Bótate RANGE switch for máximum on scale meter tíeflection (usually 5.0).
(g)
Depress CHANNEL SELECTOR to CHANNEL 1.
(h)
Following step (i) applies to vibration meter LTCT9281.
(i)
Set meter for the test as follows: 1 Set INPUT NETWORK selector to proper number for fitterto be used, as required by data sheet. 2
Set OPERATION selector to Dxl .0.
2 Set CHANNEL SELECTOR t o l . 4 Set range selector to 5. NOTE:
(j)
Opérate engine at Ni and N2 speeds shown on data sheet. NOTE:
(k)
Ground operation at high power seftings may not be possible. Aircraft must be hovered or flown to accomplish a complete vibration test.
Stabilize engine conditions by maintainlng each required engine speed for at least 30 seconds before meter indications are recorded.
At each speed setting, record meter indications on data sheet as follows; 1
Set INPUT NETWORK selector to proper number for meter network and filter to be used, as required by data sheet.
2
Set CHANNEL selector to proper number for meter channel and pickup to be used, as required by data sheet.
2 Record meter indications in proper space on Engine Vibration Test Data Sheet.
71 00-00 -
Page 2i Sept 30/02
HoneyweII
MAINTENANCE MANUAL T53-L-703
TURBOSHAFT ENGINE VIBRATION TEST DATA SHEET Engine Seriol No..
í TSN).
Lojt Ovefl^QuI
f TSLOj.
LoctJtiort
A/C Time.
Aircroft Serial No. _
Dote _
Tesi I o»-arion
Observer . Engine Foiled Test
TEensgf iende BPyo_s_s_e_o_ T __ est • Accepted
N“ Speed 1
n
P ercen t ii 0.5%)
N '1 S p e e d
No. 1 Pickup
No. 2 P ickop
S/N
S/N
• n Pe
MED' U M bCORlN C,
LIG- IT SCOBiNf i
LIGHT PlTTl NG
XA-738-201B
Gear Inspection Figure 204
72-10-01
Page2l1 Sept 30/02
HoneyweII MA,NTENANCEMANUAL 4.
Inspection and Renair Torauemeter Cvlinder and Valve A.
5.
Inspect and Repair Torquemeter Cylinder and Valve (1)
Visually inspect torquemeter valve plunger {1, Figure 204A) torquemeter valve body (2) and oil supply power takeotf nozzle assembly (3) for nicks, burrs and wear. Blend repair as outlined in SPM, 70-25-01.
(2)
Inspect torquemeter cylinder (4) for scoring and scratching on ID’s. Blend repair if sconng or scratching is 0.015 inch deep or less. Replace cylinder If defect exceeds 0.015 inch deep.
Aporoved Repairs Outout Reduction Carrier and Gear Assemblv and Sun Gearshaft A.
Repair Output Reduction Carrier and Gear Assembly and Sun Gearshaft (1)
Repair all threaded parts stripped or crossed threads. (Refer to SPM, 70-25-03, SP P409.} Replace parts having threads damaged beyond repair.
(2)
Blend repair nicks, burrs and scratches. (Refer to SPM, 70-25-01, SP R401.)
(3)
Replace all damaged parts. CAUTIQN:
(4) B.
IF A PLANET OR OUTPUT GEAR IS FOUND UNACCEPTABLE BECAUSE OF A SURFACE CONDITiON, REDUCTION GEAR ASSEMBLY SHALL BE REPLACED.
Replace reduction gear assembly and sun gearshaft that have unacceptable conditions.
Replace Forward Power Shaft Bearing CAUTIQN: THIS PROCEDURE SHALL BE ACCOMPLISHED WITH ENGINE INSTALLED IN A MAINTENANCE STAND CAPABLE OF POSITIONING ENGINE IN A VERTICAL NOSE DOWN ATTITUDE. (1)
Remove output reduction carrier and gear assembly and sun gear shaft. (See paragraph 2.)
(2)
Remove olí transfer support assembly (1. Figure 205) as follows: (a)
Remove 12 bolts (7) and washers (6).
72-10-01
Page 212 Sept 30/02
HoneyweII
MAINTENANCE MANUAL T53-L-703
1. TORQUEMETER VALVE PLUNGER 2. TORQUEMETER VALVE BODY
3.
4.
OIL SUPPLY POWER TAKEOFF NOZZLE ASSEMBLY TORQUEMETER CYLINDER
Torquemeter Parts Figure 204A
72-10-01
Page 213 Sept 30/02
HoneyweII MA,NT«MANUAL
1. 2. 3. 4.
OIL TRANSFER SUPPORT ASSEMBLY PACKING PACKING PACKING
5. 6. 7.
PACKIN G WASHE R BOLT
Oil Transter Support Assembly and Attaching Parts Figure 205
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Page 214 Sept 30/02
HoneyweII MA,NTENANCE^MANUAL (b)
Instan three 1/4-20 thread puller screws, 3 inches long, into oil Iransfer support assembly (1) and tighien screws evenly.
(c)
Remove oil transfer support assembly (1) and packings (2, 3, 4, 5),
(d)
Remove puller screws.
(3)
Remove accessory drive gearbox assembly. (See 72-60-01.)
(4)
Remove overspeed governor and tachometer drive assembly. (See 72-60-02.)
(5)
Remove accessory drive carrier assembly (1, Figure 206) as follows: (a) Instan three machine bolts LTCT1429 or LTCT109 in face ot accessory drive carrier assembly (1). Tighten machine boits evenly and remove accessory drive carrier assembly.
(6)
(7)
(b)
Remove machine bolts.
(c)
Remove oil transfer tube (2) and packings (3).
(d)
Remove packings (4, 5).
Remove power shaft bearíng retainer {see Figure 207} as foílows: (a)
Using cup remover LTCT2021, remove gear (1).
(b)
Remove ring (2).
(c)
Straighten two tabwashers (4), CAUTION: ENGINE SHALL BE POSITIONED IN VERTICAL, NOSE DOWN ATTITUDE AND REMAIN THAT WAV UNTIL BOLTS (3, 5) ARE REINSTALLED.
(d)
Remove bolts (3, 5) and tabwashers, and remove power shaft bearing retainer (6).
Disassembíe power shaft bearing retainer (see Figure 208} as follows; (a)
Remove bolts (1} that secure píate (2} to retainer assembly (4). Remove píate.
72-10-01
Page 2i5 Sept 30/02
HoneyweII
MAINTENANCE MANUAL T53-L-703
Ki
XÁ.73S-
1. 2. 3.
ACCESSORY ORIVE CARRiER ASSEMBLY OIL TRANSFER TUBE PACKING
4. PACKING 5. PACKING
Accessory Orive Carrier Assembly Figure 206
72-10-01
Page216 Sept 30/02
HoneyweII
1, 2, 3. 4.
GEAR RING BOLT TABWASHER
MAINTENANCE MANUAL T53-L-703
5. 6. 7.
BOLT POWER SHAFT BEARING RETAINER POWER SHAFT
Power Shatt Bearing Retainer Figure 207
72-10-01
Page 217 Sept 30/02
HoneyweII
MAINTENANCE MANUAL T53-L-703
4
1. 2.
BOLT CLAMPING PLATE
3. ROLLER BEARING 4, RETAINER ASSEMBLY
Power Shaft Bearing Retainer Figure 208
72-10-01
Page 218 Sept 30/02
HoneyweII MA,NTENANCE^MANUAL (b) (8)
Using suitable sieeve and arbor press, press bearing (3) from retainer assembly (4).
Reassemble power shaft bearing retainer as follows; (a)
Place retamer assembly (4) on a bench, large end down.
(b) (c)
Press bearing (3) inio bearing retainer assembly and seat firmiy. Measure from edge of bearing retainer assembly down to bearing outer race and record depth measurement.
(d)
Select píate (2) with hub height that will provide 0.001 to 0.0035 inch pinch on bearing.
(e)
Instan píate and secure with three bolts (1). Tighten bolts 40 to 45 inch-pounds torque and lockwire.
(9} Instan power shaft bearing retainer (see Figure 207) as foílows.(a)
(b)
Prior to bearing retainer installation, inspect bearing journal of powershaft for indenting, wear track or corrosión pitting. Limits are as follows: 1
Indenting and wear track are unacceptable it they can be detectad with a 0.040 inch radius scribe.
2
Corrosión pitting is unacceptable if it can be detected with a 0.020 inch radius scribe.
3
If limits are exceeded, forward engine to an Honeyweil approved Service Center.
Prior to bearing retainer installation apply shortening (72-00-00, 38, Table 203) to bearing and using installation tool LTCT14773, slide power shaft bearing retainer (6) onto power shaft (7). Using a mallet, position retainer in inlet housing with cutouts for accessory dnve driven gears in corred position, NOTE:
Do not lubrícate bolts.
(c)
Instan four bolts (3) and two tabwashers (4) with two bolts (5). Tighten bolts 70 to 95 inch-pounds torque.
(d)
Lock tabwashers on two bolts. Lockwire four bolts.
(e)
Instan retaining ring (2) in groove on power shaft. WARNING- TO PREVENT INJURY TO PERSONNEL. TEMPERATURE RESISTANT GLOVES MUST BE WORN.
(f)
Heat gear in oven for 30 minutes at 300 to 400^F (149 to 204^C). Place gear on installation tool LTCT4576. Remove gear from oven and quickiy install on power shaft spiine, seating it firmiy over retaining ring. If combustor turbine assembly ís not instaded, power shaft must be pressed forward from aft end of engine.
(g)
After installation of gear (1), measure from forward face of power shaft (7) to fonward face ofgear(l). Dimensión shall be 2.020 to 2.040 inches. (See Figure 209.)
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HoneyweII
MAINTENANCE MANUAL T53-L-703
Gearto Power Shaft - Installation Dimensión Figure 209
72-10-01
Page 220 Sept 30/02
HoneyweII ^-AINTENANCEMANUAL (10)
Instan accessory drive carrier assembly (see Figure 206) as follows: (a)
Instan two packings (4) and one packing (5) on inlet housing.
(b)
Install two packings (3) on oil transfertube (2) and install tube in accessory drive carrier assembly. NOTE:
If accessory drive carrier assembly meets sudden resistance, do not torce installation; remove carrier. inspect oil transfer tube for damage, replace packing and repeat step (c). If pilot interterence is encountered, dimensionally measure diameters and rework carrier mounting flange if necessary. During and after installation. use an inspection mirror and light and check that spur gears are properly meshed and that tachometer drive gear is in proper axial relationship wlth spur gear.
(c)
Position accessory drive carrier assembly in inlet housing using care to assure oi) transfer tube atignment and proper meshing of spur gear (1. Figure 207) and its mating tachometer drive spur gear in the accessory Orive carrier assembly.
(11)
Install overspeed governor and tachometer drive assembly. (See 72-60-02.)
(12)
Install accessory drive gearbox assembly. (See 72-60-01.)
(13)
Install oil transfer support assembly (see Figure 205) as follows: (a) Install packings (2, 3, 4, 5) on rim of accessory drive carrier assembly and on hm of oil transfer support assembly. NOTE: (b)
(14)
Do not lubrícate bolts.
Position oil transfer support assembly (1) on flange of accessory drive carrier assembly and secure wlth 12 bolts (7) and washers (6), Torque bolts as required. Lockwire bolts.
Install output reduction carrier and gear assembly and sun gearshaft. (See paragraph 3.)
72-10-01
Page 221/222 Sept 30/02
HoneyweII MAINT^MANUAL TQRQUE METER CYLINDER AND TOROUEMETER VALVE ASSEMBLY - DESCRIPTION AND OPERATION 1. Description and Qoeration The torquemeter valve assembly is Installed on the torquemeter cylinder. The assembly is used to check pressure from accessory gearbox.
72-10-02
Page 1/2 Sept 30/02
HoneyweII ‘^A.NTENAN^MANUAL TORQUEMETER CYLINDER AND TORQUEMETER VAIVF ASSEMBLY - MAINTENANCE PRACTICES 1. Removal/InstallatiQn Cvlinder and Torauemeter Valve Assemblv A.
B.
Remove Torquemeter Cylinder and Torquemeter Valve Assembly (1)
Using installer and remover LTCT519 or socket (preferably 6 point), remove torquemeter valve assembly (1, Figure 201) shim (2) from torquemeter cylinder (4).
(2)
Remove 12 bolts (3) that secure torquemeter cylinder (4). Remove cylinder from miel housing assembly.
Instan Torquemeter Cylinder and Torquemeter Valve Assembly CAUTIDN:
DO NOT OVERTIGHTEN AS TRIS WILL CAUSE DISTORTION. TORQUE TO PROPER SPECIFICATION.
(1)
Instan torquemeter cylinder (4) and secure with bolts (3).
(2) (3)
Instan shim (2) on torquemeter valve assembly (1). Usmg installer and remover LTCT519 or socket (preferably 6 point) install torquemeter valve assembly (1) into torquemeter cylinder. Tighten valve 150 to 200 inch pounds torque.
(4)
Using depth micrometer or depth gage, measure dimensión from end of torquemeter cylinder to forward face of mounting fiange (see Figure 202). If not within 0.265 to 0.275 inch, replace cylinder.
(5)
Using depth micrometer or depth gage, measure distance (Dimensión A, Figure 203) from forward end of inlet housing torquemeter valve plunger and distance (Dimensión B) from forward end of inlet housing to inner fiange of torquemeter cylinder. NOTE:
Dimensión C shall be within 0.030 to 0.034 inch. If this dimensión is not within limits, remove torquemeter valve, shim as required and reinstall valve and shim.
Subtract Dimensión A from Dimensión B to obtain Dimensión C. (6)
Lockwire torquemeter valve assembly.
72-10-02
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HoneyweII
MAINTENANCE MANUAL T53-L-703
VA
1. 2.
TORQUEMETER VALVE ASSEMBLY SHIM
3. BOLT 4. TORQUEMETER CYLINDER
Torquemeter Cylinder and Torquemeter Valve Assembly Figure 201
72-10-02
Page 202 Sept 30/02
HoneyweII *^A,NTENANCEMANUAL
Torquemeter Cylinder Measurement Figure 202
72-10-02 r
Page 203 Sept 30/02
HoneyweII
1.
TORQUEMETER CYLINDER
2.
SHIM
MAINTENANCE MANUAL T53-L-703
3, TORQUEMETER VALVE
Torquemeter Valve Location and Adjustment Diagram Figure 203
72-10-02
Page 204 Sept 30/02
HoneyweII COMPRESSOR AND IMPELLER HQUSING ASSEMBLIES - DESCRIPTIQN AND OPERATION 1.
Description and Qoeration Compressor and impeller housings each consist of two halves. Housings endose five-stage axial compressor and single-stage centrifuga! compressor impeller of compressor rotor assembiy. Axial compressor stator vane assemblies are bolted to compressor housing halves. An air-bleed actuator is mounted on the right side of the impeller housing. An air-bleed connecting manifold and adapter assembiy ducts bleed air from the diffuser housing to the inlet housing for anti-icing. Customer air is available from this adapter assembiy.
72-30-01
Page 1/2 Sept 30/02
HoneyweII MMNTENANCEMANUAL COMPRESSOR AND IMPELLER HOUSING ASSFMBLIES - MAINTFNANCE PRACTICFS 1. Removal/lnstallation Compressor and Imoeller Housino Assemblies CAUTION: ONLY ONE HALF OF COMPRESSOR AND IMPELLER HOUSING MAY BE REMOVED ATA TIME. A. Remove Compressor and Impeller Housing Assemblies NOTE:
When a bracket is released by removal of a bolt, secure boit, washer and nut to bracket until ready for installation. To tacllitate installation of housings, identify and mark position of all removed ítems.
(1)
Remove Unes, hoses and accessories as necessary.
(2)
Remove nuts (27, Figure 201) washers (26) and bolts (2) from four locating doweis (1) on compressor housing assembly flanges.
(3)
Using mechanical puller LTCT1218 remove four doweis (1).
(4)
Remove 12 nuts (25), washers (24). bolts (4) and washers (3) that secure compressor housing assembly upper half (8) to lower half (23).
(5)
Remove 10 bolts (6) and washers (5) that secure compressor housing assembly half (8 or 23) to inlet housing assembly.
(6)
Remove one bolt (7) and eight bolts (18) and washers (17) or nine bolts (18) and nine washers (17) that secure compressor housing assembly half (8 or 23) to impeller housing assembly hall (11 or 22). CAUTION:
IMPELLER HOUSING ASSEMBLIES HAVE PILOT FLANGES THAT FIT INTO COMPRESSOR AND DIFFUSER HOUSING ASSEMBLIES. TO PREVENT DAMAGING THESE FLANGES DURING DISASSEMBLY, ALWAYS REMOVE COMPRESSOR HOUSING ASSEMBLY HALF BEFORE ATTEMPTING TO REMOVE IMPELLER HOUSING ASSEMBLY HALF.
(7)
Using four 1/4-28 bolts, AN-4 or equivalent, as jackscrews, remove compressor housing assembly half (8 or 23).
(8)
Remove nuts (20), washers (21) and bolts (12) from two locating doweis (13) on impeller housing assembly flanges.
(9)
Using adapten LTCT6740 and mechanical puller LTCT1218, remove two doweis (13).
72-30-01
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HoneyweII
Compressor and Impeller Housing Assemblies Figure 201
72-30-01
Page 202 Sept 30/02
HoneyweII
MAINTENANCE MANUAL T53-L-703
KEY TO FIGURE 201 1. 2. 3. 4. 5. 6. 7. 8. 9. 10. 11. 12. 13. 14.
DOWEL BOLT WASHER BOLT WASHER BOLT BOLT COMPRESSOR HOUSING ASSEMBLY UPPER HALF BOLT WASHER IMPELLER HOUSING ASSEMBLY UPPER HALF BOLT DOWEL BOLT
WASHER BOLT WASHER BOLT NUT NUT WASHER
22. IMPELLER HOUSING ASSEMBLY LOWER HALF 23. COMPRESSOR HOUSING ASSEMBLY LOWER HALF 24. WASHER 25. NUT 26, WASHER 27. NUT
(10)
Remove two nuts (19) and bolts (14) that secure impelier housing assembly upper hall (11) lovver half (22).
(11)
Remove two bolts (9), two washers (10), 10 bolts (16) and 10 washers (15) or 12 bolts (16) and 12 washers (15) that secure impelier housing assembly half (11 or 22} to diffuser housing assembly. CAUTION:
(12)
B.
15, 16, 17, 18, 19. 20. 21.
DO NOT ALLOW IMPELLER HOUSING ASSEMBLY HALF TO STRIKE IMPELLER OR COMPRESSOR BLADES. SUCH CONTACT MAY DAMAGE BLADES OR INNER SURFACE OF HOUSING ASSEMBLY
Move impelier housing assembly half (11 or 22) toward inlet housing assembly; then lift and remove.
Instan Compressor and Impelier Housing Assemblies (1)
Instan impelier housing assembly upper half (11, Figure 201) or lower half (22).
(2)
Make sure that a gap of 0.010 inch minimum will exist between shroud ends of mating vane assemblies after compressor housing installation. File shroud end. as required, to obtain clearance and install compressor housing.
(3)
Coat mating surfaces of compressor housing and impelier housing with non drying zinc chromate seaiant (72-00-00, 75, Table 203). Install compressor housing assembly upper half (8) or lower half (23). Install hollow doweis (1. 13) and secure upper and lower halves of impelier and compressor housings with nuts (20, 27). washers (21,26) and bolts (2, 12). Tighten nuts to 70 to 95 inch-pounds torque.
72-30-01
Page 203 Sept 30/02
HoneyweII (4)
Apply non drying sealant (refer to SPM, PJ26, SP P526) under bolts and install bolts (6) and washers (5) ihat secura compressor housmg assembly half (8 or 23) to inlet housing assembiy.
(5)
Position clips for air bieed band on proper bolts. Apply sealant under heads of bolts and nuts, on both taces of washers and in bolt cavities. Install bolts (7, 18} and washers (17) that secure compressor housing half (8 or 23} to impeller housing half (11 or 22). Tighten botts to proper torque and lockwire. Atter assembly is completed, wipe off excess sealant with deán cloth dampened in toluene (72-00-00, 66, Table 203). NOTE:
2.
MAINTENANCE MANUAL T53-L-703
Position bracket for ignition unit under three bolts (16) at approximately 10 o’clock position.
(6)
Install 12 bolts (9, 16) and washers (10, 15) that secure impeller housing assembly half (11 or 22) to air diffuser housing assembly (see Figure 202). Tghten bolts (9, 16, Figure 201} and lockwire.
(7)
Install bolts (14) and nuts (19) that secure upper and lower halves of impeller housing assembly. Tighten bolts and lockwire.
(8)
install bolts (4), washers (3, 24) and nuts (25) that secure upper and lower halves of compressor housing assembly. Tighten bolts and lockwire.
(9)
Make sure that all removed brackets have been reinstalled and install all removed lines, hoses and accessories.
Disassembiv./Reassemblv Compressor Housing Assembly NOTE:
The procedure applies to either half of compressor housing assembly.
A. Disassemble Compressor Housing Assembly (1) (2)
Place compressor housing assembly half on bench and secure to bench to prevent movement. Remove bolts (4, 5,14,16, Figure 203) and washers (3. 6, 15, 17) that secure first through fourth stage compressor vane assemblies (8, 10. 11, 12). Remove vane assemblies.
(3)
Remove two bolts (1) and bolt retainers (2) and three bolts and washers (19) that secure exit guide vane assembly (13). Remove vane assembly.
B- Reassemble Compressor Housing Assembly NOTE:
Rematched stator vane assemblies shall meet all assembly requirements. Halves of rematched stator shall have approximately the same degree of foreign object damage or erosión, within established limits; an eroded stator half shall not be rematched with a noneroded half.
(1) With removed half of compressor housing assembly on bench, reinsert first through fourth stage compressor vane assemblies (8, 10, 11, 12, Figure 203) and exit guide vane assembly (13) into their appropriate slots.
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MAINTENANCE MANUAL T53-L-703
INSTALL BOLTS ( MS9530 -13I ANO W ASHERS (AN960 -416L) IN TW O LOCATIONS MARKED
A
Impeller Housing Bo!t Locations Figure 202
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Compressor Housing Assembly Figure 203
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HoneyweII MA,NTENANCE^MANUAL KEY TO FIGURE 203 1. 2. 3. 4, 5, 6, 7. 8. 9. 10.
BOLT BOLT RETAINER WASHER BOLT BOLT WASHER UPPER COMPRESSOR HOUSING FIRST STAGE COMPRESSOR VANE ASSEMBLY LOWER COMPRESSOR HOUSING SECOND STAGE COMPRESSOR VANE ASSEMBLY
11. THIRD STAGE COMPRESSOR VANE ASSEMBLY 12. FOURTH STAGE COMPRESSOR VANE ASSEMBLY 13. EXIT GUIDE VANE ASSEMBLY 14. BOLT 15. WASHER 16. BOLT 17. WASHER 18. BOLT 19. WASHER
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HoneyweII (2)
(3) 3.
Secure compressor vanes to compressor housing half as follows: (a)
Tighten first through fourth stage vanes with bolts (4, 5, 14, 16), washers (3. 6, 15, 17). Tighten center bolts 44 to 46 inch pounds torque. Tighten outside bolts 14 to 16 inch pounds torque. (See Figure 204.)
(b)
Tighten exit guide vane with bolts (18, 1, Figure 203), washers (19) and bolt retalners (2). Tighten center bolts 44 to 46 inch pounds torque. Tighten outside bolts 14 to 16 inch pounds torque. Tighten bolts (1) 30 to 40 pound inches torque (see Figure 204). Make sure that a gap of 0.000 to 0.010 inch exists between the exit guide vane and the fifth stage inserí. (See Figure 205.)
Lockwire bolts and deform retainers into slot in cap screw and Slot in housing.
Insoection/Check Compressor and Imoeller Housino Assemblies A. Inspect Compressor and Impeller Housing Assemblies (1)
Inspect compressor housing assembiy. (a)
Visually inspect for nicks and burrs. Repair.
(b)
Visually inspect for foreign material deposite,
(c) (d)
Visually inspect for cracks. (Refer to SPM, 70-20-04, SP 1304.) Visually inspect housing halves for broken alignment ears. Replace Housing Return engine to Honeyweil approved Service Center. NOTE:
(e) (2)
If corrosión is present on the aft flange of the axial housing. Return engine to authorized Service center or facility capadle of installing the stainless Steel shim. (Refer to 72-09-30, Repair Manual.)
Visually inspect for corrosión. Repair,
Inspect vane assemblies. (a)
Visually inspect for cracks. Cracks are not allowed other than in the vane to shroud brazement; any number up to 1/8 inch ¡n length are acceptable.
(b)
Visually inspect stator vanes for deformatlon. Repair.
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MAINTENANCE MANUAL T53-L-703
VERTICAL CENTERLINE
FORWA RO
OF ENGINE
üghtening Compressor Housing Vane Assembly Boits Figure 204
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Exit Guide Vane Assembly Gap Figure 205
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HoneyweII (c) (3)
Visually inspect vanes lor nicks, burrs, pits and dents. Repair.
Inspect impeller housing assembiy. (a)
Inspect for nicks, dents and rubs. Small scatlered nicks and dents up to 0.010 inch in depth allowed. Blend repair {refer to SPM, 70-00-29, SP R401)- Slight rubs up to 0.005 inch in depth are allowed.
(b)
Inspect for corrosión. (See Figure 206.) NOTE:
4.
MAINTENANCE MANUAL T53-L-703
Repair corrosión in steps 1 through 4 which are within limits.
1
Corrosión pitting on ID/OD contour wall thickness shall not exceed 0.010 inch deep. Replace if limits are exceeded.
2
Mínimum ID/OD contour wall thickness must exceed 0.070 inch. Replace if limits are not met.
3
Corrosión on forward/aft mounting flange shall not exceed 0.030 inch. Replace if limits are exceeded.
4
Corrosión on axial ribs shall not exceed 0.030 inch deep. Replace if limits are exceeded.
Aporoved Repairs Comoressor and Impeller Housina Assemblies A. Repair Compressor Housing Assembiy CAUTION: DELETED. (1)
Blend repair nicks and burrs from compressor housing. (Refer to SPM, 70-25-01, SP R401.)
(2)
Deleted.
(3)
Deleted.
(4)
Deleted.
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MA!NTENANCE MANUAL T53-L-703
OO CONTOUH
XA 1333-117
Housing Repair Limits Figure 206
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HoneyweII MA,NT„MANUAL B.
Repair Stator Vane Assembly NOTE:
If damage on only one half of a compressor vane assembly exceeds the máximum permissible limits, only that affected assembly haif shatl be replaced. Stator vane halves remaining after other halves have been rejected can be matched with another serviceable half provided the replacement half has approximately the same amount of erosión or FOD. Rematched stator vane assemblies shall meet all assembly requirements.
(1) Blend repair stator vane assembly as follows: NOTE:
Blend repair shall be made with small diesinker type files and India or carborundum stones. Abrasive crocus cloth (72-00-00, 13, Table 203) shall be used for final polishing. Power tools shall not be used. All repairs shall be blended and finished smoothly. The finish strokes of all repair work shall be parallel to the leading edge of the vane, The aggregate repair length on any one vane leading or trailing edge Shall not exceed 40 percent of its length.
(a)
Dents with smooth contours are acceptable without rework provided that they do not exceed repair limits. (See Figure 207.)
(b)
Nicks, burrs, pits and rough dents on the airfoil shall be blend repaired provided that damage after repair does not exceed limits given.
(c)
Nicks and dents up to 0.080 inch deep after repair are permitted on the leading and trailing edge. Length of repair shall be at least twice and not more than four times, the depfh.
(d)
Nicks and dents on vanes in inaccessible areas of repair are acceptable without rework provided that they do not exceed máximum permissible limits.
(e)
Bent vanes shall be straightened, usmg padded pliers or equivalent. If the straightenmg causes a crack in the vane, the assembly half shall be replaced.
(f)
All stator vane halves remaining after other halves have been rejected can be rematched with another serviceable half. Rematched stator vane assemblies sha)) meet al) assembly requirements and shatl have approximately the same degree of foreign object damage or erosion. An eroded stator half shall not be rematched with a non eroded half.
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I
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MAINTENANCE MANUAL T53-L-703
Compressor Stator Vane Repair Límits Figure 207
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MAINTENANCE MANUAL
T53-L-703
COMPRESSOR ROTOR AND IMPELLER ASSEMBLY - DESCRIPTION AND OPERATION 1. Descriotion and Operation The compressor rotor assembly consists of a stainless Steel front shaft assembiy. stainless Steel compressor rear shaft and a one piece titanium impelier, ai! of which are bolted to an electrón beam welded axial compressor spool consisting of the second through fifth stages of the axial compressor. The gas producer rotor assemblies are mounted on the rear compressor shaft of the compressor rotor assembly. The compressor rotor assembly endoses, but is not connected to, the power shaft.
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MAINTENANCE MANUAL T53-L~703
COMPRESSOR ROTOR AND IMPELLFR ASSEMBLY - MAINTENANCE PRACTICES 1. Inspection/Check Comoressor Rotor and Impeller Assemblv A. Inspeci Compressor Rotor Biades (1)
Visually inspect biades for bends or distortion. CAUTION; IF CRACKS ARE FOUND ON ANY FiRST STAGE BLADE, SCRAP ALL FIRST AND SECOND STAGE BLADES. REPLACE WITH NEW BLADES.
(2)
Using a strong light source and 7 10 power magnifier, visually and if crack indications are noted, fluorescent penetrant inspect biades for cracks (refer to SPM. 70-20-05. SP 1305). No cracks allowed. Replace detective biades.
(3)
Visually inspect biades for nicks, burrs, dents and other foreign object damage. NOTE:
(4)
To facilítate rework, all damage or defects shall be identified and marked with an approved marking pencil (72-00-00, 47, Table 203).
Inspect all compressor biades for corrosión and pitting. Pitting is allowed provided. (a)
The major diameter of any pit does not exceed 0.015 inch (0.38 mm).
(b) (c)
The distance between pits is a minimum of five times the major diameter. Confirm that pits are corrosión and not erosión or impact damage using magnification as required. Replace all detective biades.
NOTE:
Varnish will appear as dark film, consisting of oil and dirt deposits that have hardened on biade surfaces.
(5)
Visually inspect biades for varnish buildup.
(6)
Inspect first stage biades for inlet blockage. (See 72-00-00, ENGINE - INSPECTION.) NOTE:
Rolled over effect can be detectad by running a fingernail along airfoil
on convex side until leading edge is contacted. (7)
Using standard inspection equipment, inspect leading edge of biades for undercufting, erosión roughness and slight rolled over effect. (See Figure 201.)
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MAINTENANCE MANUAL T53-L-703
Blade Repair Limits for Undercutting, Erosión and Rolled Over Affect Figure 201
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MAINTENANCE MANUAL
nori©ywVdi
(8) B.
C.
T 53- L -703
(a)
Using a straight edge (6 inch scale or equivaient) placed slightiy above platform radios, and a 0.0156 inch wire gage used as a GO or NO GO device, determine degree of undercutting (see Figure 202). A máximum of 0.0156 inch is permissible along leading edge area between platform radius and tip. A wavy pattern (more than one undercut area) is unacceptable. If within limits, repair by stoning blades on leading edge oniy (from blade tip to critical area) to remove Sharp projections and roll over burrs. Strokes shall be parallel to leading edge.
(b)
Erosión roughness and roll over etfect is acceptable provided previous requirements and requirements in following step (8) are met.
Measure chordal width at midpoint of blades. Blades is acceptable for further use if chordal width is 0.962 inch or greater (see Figure 202). If limit cannot be met, replace defectiva blades.
Inspect Centrifugal Compressor Impeller Assembly (1)
Visually inspect blades for nicks, cracks or bending in the critical area (see Figure 203). No repair allowed. Smooth dents are acceptable provided they do not exceed 0.040 inch in diameter and 0.010 inch in deplh.
(2)
Visually inspect blades for cracks or bending in noncritical areas. No repair allowed. Minor dents and nicks are permitted and should be reworked provided a 0.025 inch blade thickness remains. Repair centrifugal compressor impeller assembly or replace, as required.
(3)
Inspect leading edge of blades for erosión. Using a straightedge placed across the forward lip of the centrifugal impeller, determine size of gap between straightedge and impeller blade (see Figure 204). A máximum gap of 0.093 inch is permissible. Measure all blades. Reject impeller if a rejected blade is found.
(4)
Deleted.
inspect Compressor Rotor Assembly (1) Inspect rotor areas between blades (spacer area). Minor nicks and dents are permitted without repair.
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MAINTENANCE MANUAL T53-L-703
MEASURE CHORDAU WIDTH HERE (0.962 INCH OR GREATER) AT 6LADE MtDPOINT
XA-1338-173
Blade Limits for Undercutting Figure 202
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MAINTENANCE MANUAL T53-L-703
AIRFOIL (SIDES) 0.025 IN. TH1CKNE5S MUST REMAIN AFTER REPAIR
■ 13J8 IKA
Centrrfugal Impeller Repair Limits Figure 203
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IMPELLER VANE
XA 1338-126
Centrifugal Impelier Btade Erosión Limits Figure 204
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HoneyweII MAINTENANCE^MANUAL (2) Inspect blade retention areas. Damage other than minor well spaced nicks and dents is not allowed. Blend repair (refer to SPM, 70-25-01, SP R401) oí nicks only to e>ctent of removing Sharp protrusions is permitted where access permits. D.
Inspect Clearance Of Compressor Rotor and Centrifugal Impeller (1) Inspect for proper clearance as íollows: NOTE:
(a)
When taking blade tip clearances, insert feeler gage 1/4 to 1/2 inch below the compressor housing flange line.
Using 12 inch feeler gage, take radial blade tip clearances of five compressor stages. Take two clearance readings, 180 degrees apart, for each rotor stage. Take clearance readings from compressor rotor blade tips to compressor housing. Rotate compressor rotor one full turn while taking clearance at each of the ten checkpoints. (See Figure 205.) 1 Radial tip clearance for compressor rotor blades:
(b)
a
First stage
0.018
mínimum.
b
Second stage
0.018
minimum.
c
Third stage
0.024
minimum.
d
Fourth stage
0.024
minimum.
e
Fifth stage
0.024 minimum.
Using a 12 inch feeler gage, check radial clearance of four compressor vane assemblies and exit guide vane assembiy. Take clearance readings from compressor stator vane to compressor rotor spacers as follows: 1
Take two clearance readings, 180 degrees apart from front of first stage compressor vane assembiy to first stage compressor rotor spacer. Rotate compressor rotor one full turn while taking clearance readings at each of these two checkpoints.
2
Take two clearance readings, 180 degrees apart from rear of first stage compressor vane assembiy to first stage compressor rotor spacer. Rotate compressor rotor one full turn while taking clearance readings at each of these two checkpoints.
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MAINTENANCE MANUAL T53-L-703
Radial Tip Clearances Figure 205
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HoneyweII 3
Take two ciearance reaOings, 180 degrees apart, at front and rear oí each compressor vane assembly ío each compressor rotor spacer lor the seoond through lifth rotor stages. The exit guide vane assembly requires oniy one ciearance readlng at the front. Roíate compressor rotor one (ull turn while taking ciearance readings at each of these two cheokpoints. (See Figure 206.)
4
Radial clearances between compressor vane assemblies and compressor rotor spacers are as follows; a First through fitth stage 0.026 minimum ciearance.
(c)
Using 12 inch feeler gage, take axial ciearance of compressor rotor disc assemblies lo compressor vane assemblies for first through fitth stages. Take two ciearance reaOings, 180 degrees apart, for each compressor rotor stage. Roíate compressor rotor one tuil turn while taking ciearance readings at each of the 18 cheokpoints. (See Figure 206.) NOTE:
If clearances are not within limits. release torque and relorque bolts.
1 Axial clearances between compressor rotor disc assemblies and compressor vane assemblies are as follows:
(d)
a
First rotor to first vane
0.040 inch minimum.
b
First vane to second rotor
0.040 inch minimum.
c
Second rotor to second vane
0.040 inch minimum.
d
Second vane to third rotor
0.040 inch minimum.
e
Third rotor to third vane
0.040 inch minimum.
f
Third vane to fourth rotor
0.040 inch minimum.
g
Fourth rotor to fourth vane
0.040 inch minimum.
h
Fourth vane to fifth rotor
0.040 inch minimum.
i
Fitth rotor to exit guide vane
0.029 inch minimum.
Using 12 inch feeler gage, take two axial ciearance readings, 180 degrees apart, between impeller assembly and exit guide vane assembly. Roíate compressor rotor one full turn while taking ciearance readings at each of the remaining cheokpoints.
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Axial Clearance of Compressor Rotor Disc Assembly Figure 206
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1 Axial clearance between impeller assembly and exit guide vane assembly is exrt guide vane assembly to impeller assembly 0.048 inch mimmum clearance. (e)
Using 12 inch feeler gage, take radial tip clearance from centrifugal compressor impeller assembly blades to impeller housing assembly. Rotate compressor rotor one full turn while taking clearance readings at each of the six checkpoints. 1 Tip clearance between impeller blades and Impeller housing assembly are as lollows:
Impeller Blades Impeller Housing Assembly
Direction
Housing Clearance (Inches) Mínimum
NOTE: All clearances are measured with bearing end play taken up in a forward direction. Centrifugal Compressor Impeller Radial Assembly to Impeller Housing Assembly (Forward End of Impeller Blade)
0.023
Centrifugal Compressor Impeller Radial Axial Assembly (Midpoint) of Impeller Blade)
0.037
Centrifugal Compressor Impeller Axial Assembly to Impeller Housing Assembly (Rear of Impeller Blade)
0.052
Exit guide Vane to Impeller Housing
Axial
inleí Guide Vane to First Rotor
Axial
Impeller Blades to Diffuser Housing Axial
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THIRO, FOURTH ANOFIFTH STAGE BLADES
FIRST AND SECOND STAGE BLAOES
GREATER THAN 3/32 INCH
3/32 INCHOR LESS
REPAIRED
3/32 INCH
75 PERCENT OF ORIGINAL BLAOE TMICKNESS MUST REUAIN AFTER REPAIR
MINIMUM Of 1/2 TIP CHORDAL WIDTH MUST REMAIN AFTER REPAIR
COMPRESSOR BLADE MAXIMUM ALLOWABLE DEPTH S AFTER BLAOE REPAIR BLENO LEADING TRAILINO EDOES
75 PERCEHT OF ORIGINAL BLADE THICKNES5 MUST REMAIK AFTER REPAIR
3/32 INCH ORLESS
SECTION A-A
♦
SECTION
C-C
1.7MI73A
Compressor Rotor Blade Damage Before and After Repair (All Stages) Figure 207
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Honeywell -—-NUAL
(2)
(d)
Repairs to damage within 1/8 inch of blade tip shail be continued to tip. (See Figure 207.)
(e)
If distance between two damaged areas is less than 3/32 inch, make one blend repair. If distance is greater than 3/32 inch, make sepárate repairs.
Finished repairs on blade tip edges (see Figure 207) shall be limited as tollows: (a)
Máximum allowable repair depth is 3/32 inch.
(b)
Minimum allowable repair length is three times repair depth. NOTE:
(c)
(3)
A minimum of 1/2 of blade tip chordal width musí remain after blend repairs. (See Figure 207.)
If damage is closer to tip edge than 1/16 inch. blend repair to leading or trailing edge, whicbever applies.
Finished repairs to blade airfoil surfaces shall be limited as follows; (a)
Minimum airfoil thickness after repair shall be three fourths original thickness.
(b)
If distance between two damaged areas is less than 3/32 inch. make one blend repair. If distance is greater than 3/32 mch, make sepárate repairs.
(c)
Máximum allowable repair length on blade airloil areas shall be 13/32 inch.
(d)
Remove scratches or lines in airloil areas. Repairs shall be within limits.
(e)
No more than 20 percent of total blade material may be removed during repairs.
CAUTION:
DO NOT ATTEMPT TO STRAIGHTEN BENT OR DISTORTED BLADES.
(4)
If damage or repair dimensions exceed allowable limits. replace blade.
(5)
Replace bent or distorted blades.
(6)
Remove varnish on airfoil surfaces as follows: NOTE:
(a)
Lapping compound is prepared by mixing 1 part aluminum oxide, Grade 400 (72-00-00, 5. Table 203) by volume with 3 parts cutting oil (72-00-00, 22, Table 203).
Place lapping compound on soft cotton cloth. CAUTION:
MAKE SURE THAT BLADES ARE RUBBED ONLY IN A RADIAL DIRECTION (PARALLELTO LEADING EDGE).
(b)
Using thin piece of wood or plástic to suppon the cloth. rub blades to remove varnish buildup.
(c)
Reinspect all blades to make sure that varnish buildup has been compietely removed. Repeaf preceding steps (a) and (b), if necessary.
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HoneyweII (d)
B.
Remove all traces of lapping compound with soft cotton cloth moistened with dry cieaning sotvem (72-00-00, 62, Table 203).
Removal of Compressor Rotor Blades NOTE:
(1)
First stage rotor blades are removed rearward. Second through fifth stage rotor blades of compressor rotor subassembly are removed in a forward direction,
Remove upper compressor and impeller housings. (See 72-30-01.) CAIJTION:
MAKE SURE TO HOLD LOCKING PLATE AND BLADES SECURELY TO AVOID DROPPING THEM BETWEEN INLET GUIDE VANE AND FIRST STAGE COMPRESSOR ROTOR DISC OR INTO LOWER COMPRESSOR ROTOR HOUSING. DO NOT ALLOW TOOLS TO CONTACT COMPRESSOR DISC AREA.
(2)
Inserí drift LTCT1643 through front of inlet housing and through inlet guide vane to contact base of damaged first stage rotor blade. Inlet guide vane may be moved as necessary to facilítate blade removal. Gently tap remover to remove blade from disc. Remove and discard locking píate after blade removal. Remove pin if damaged. CAUTION:
(3)
WHEN A DAMAGED FIRST STAGE ROTOR BLADE IS TO BE REPLACED, THE 16TH BLADE LOCATED COUNTERCLOCKWISE FROM DAMAGED BLADE LOCATION AS VIEWED FROM REAR OF FIRST STAGE ROTOR DISC MUST ALSO BE REMOVED TO MAINTAIN PROPER ROTOR BALANCE,
Using procedures in preceding step (2), remove the 16th blade located counterclockwise from damaged blade location as viewed from rear of first stage rotor disc. NOTE:
Up to ten sets of blades may be replaced if damage Is limited to ten sets or less. If more than ten blade sets are damaged, replace all blades.
(4)
Repeat procedures In step (2) until all blades that are to be replaced have been removed from first stage rotor assembiy.
(5)
On second through fifth stage rotor blades of compressor rotor subassembly, use drift LTCT1644 and gently tap blade out of disc. Remove and discard locking píate after blade removal. Remove pin if damaged. (See Figure 208.) CAUTION:
(6)
WHEN A DAMAGED SECOND THROUGH FIFTH STAGE ROTOR BLADE IS TO BE REPLACED BY A FIELO REPLACEMENT BLADE, THE BLADE LOCATED 180 DEGREES DIAMETRICALLY OPPOSITE TO DAMAGED BLADE MUST ALSO BE REPUCED TO MAINTAIN PROPER ROTOR BALANCE.
Page 215 Using procedures in preceding step (5), remove rotor blade located 180 degrees diametrically Sept 30/02 opposite from damaged blade.
72-30-02
HoneyweII NOTE:
There is no limit to the number of blade sets that may be replaced- If more than six sets of blades are replaced, an engine vibration check shall be performed. (See 71 -00- 00, paragraph 11 .E.) Return to supply all serviceable blades that have been removed in order that they may be made into replacement sets.
(7)
Repeat the procedures in steps (5) and (6) until all blades that are to be replaced have been removed from second, third, fourth or fitth stage compressor rotor subassembiy.
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Removing Compressor Rotor Blade Figure 208
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MAINTENANCE MANUAL T53-L-703
C- Inspeclion oí Blade Root Coating NOTE:
11 íacilities are not avaüable to apply graphite varnish coating to blade roots, then new blades that have coated blade roots shal! be installed.
(1)
II coating is not present or is damaged on allected blade root surtaces, graphite varnish coat compressor rotor blade roots.
(2)
Prepare blade roots lor coating as tollows: (a)
Olean blades by vapor degreasing or dry cleaning solvent method. (Reíer to SPM 70-15-01, SP 0201 and SPM, 70-15-03, SP 0203.)
(b)
Mask airloil surfaces oí blades using two stainless Steel plates 1.75 inches wide by 20 inches long by 0.060 inch thick and two pieces oí rubber 1.75 Inches wide by 18 inches long by 0.125 inch thick. {See Figure 209.) NOTE:
(3)
Slurry shall be agitated or circulated in such a manner to prevent settiing oí abrasivo.
(c)
Prepare wet abrasive slurry, 40 percent liquid abrasiva (72 - 00 - 00, 39, Table 203) by volume, balance water and vapor blast blades. (Reíer to SPM, 70-15-05. SP 0205.)
(d)
Remove masking and rinse; lirst with coid water, then with hot water heated to 160-F {71°C) mínimum. Dry in oven lor 10 minutes at 335°F (168"C).
Prepare and apply graphite varnish coating as follows: (a)
Using cardboard masks 2 inches wide by 20 inches long, mask airloil suríaces. (See Figure 210.)
(b)
Mix 1 part corrosión preventiva synthetic resin varnish (72-00-00, 69. Table 203) with 2 parts graphite suspensión (colloidal) in "dag" dispersión (72-00-00, 23, Table 203).
(c)
Apply graphite varnish (see Figure 211) as follows: 1
Using a Binks spray gun equipped with noz2le 66SD (Binks Company) or equivalent, at an air pressure of 30 psig. make passes at a modérate speed approximately 8 inches from blades.
2
Make One pass in each direction on each side.
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MAfNTENANCE MANUAL 153-1-703
STAINLESS ST PLATES
Masking Airfoil Surfaces in Preparation for Vapor Blasting of Blade Roots Figure 209
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MAINTENANCE MANUAL
T53-L-703
Masking Shieid Preparation Prior to Spraying Blade Roots Figure 210
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X A-7Se*SS7A
Coating of Blade Roots Figure 211
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MAINTENANCE MANUAL T53-L-703
3 Wait 3 to 4 minutes for solvent to evapórate.
I
4 Make a second pass in each direction on each side. 5 Air dry for at least 15 minutes or until dry to touch. (d)
Remove blades from cardboard mask and arrange in oven rack.
(e)
Cure by heating in a hot air circulated oven to 325 to 345'^F (163 to 174"’C) for 50 minutes or 300'F (149^C) for 1 to 2 hours.
(f)
Remove blades from oven and air cool.
D. Installation of Compressor Rotor Blades NOTE:
Prior to installation of compressor rotor blades in any stage, make sure that affected surfaces of roots (see Figure 211) are coated with graphite varnish If coating is not present or is damaged, blade roots must be coated with graphite varnish. (See paragraph 2.C.)
All blades replaced in ihe fleid shall be replaced in pairs, using specia/ fieid (shoríer) bíade sefs. Following is a list of fieid replacement blade sets:
NOTE:
STAGE
PART NUMBER
First Second Third Fourth Fifth
1-100-361-05 1-100-286-08 1-100-383-04 1-100-384-04 1-100-385-04
First stage compressor rotor blades are installed from the rear in a forward direction. Blades of second through fifth stages are installed from the front in a rearward direction. Fieid replacement blades will carry the symbol '‘0” vibropeened on rear face of blade root. In the event of subsequent damage to one of these blades, it may again be replaced wlthout viotating the máximum ailowabie llmits. If a blade carnes Symbol “0" with an “X’’ through it. that blade has been a fleid maintenance replacement at one time, but has since been through overhaul and may now be considered as having no symbol. If replacement blades do not have an “O" on the blade root, they shall be so marked, using a vibropeen marking tool, before they are installed. On the third. fourth, and fifth stage rotor disc, six blade sets per rotor disc may be replaced. If this number is exceeded, ship engine to Overhaul facility.
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■ IOri©y*Vdl
NOTE:
The compressor front shatt assembly has a compliment oí 31 blades and requires a special assembly procedure. The followtng steps musí be performed for blade instailation of the first stage compressor disc only. Blade weight to the nearest 0.1 gram is stamped on the convex side oí each blade. Two blades marked with equal weights are a set and are to be kept together,
(1) Pertorm the lollowing steps tor blade instailation oí compressor front shaft assembly (lirst stage disc). NOTE:
(a)
As blade set No. 8 requires three blades, take one blade from set No. 9 and place it in set No. 8. Retain other blade No. 9 as a spare. Set No. 10 becomes set No. 9, set No. 11 becomes 10, etc., as only 15 sets are required tor instailation.
Blade sets are to be arranged in a row according to ascending weights. STEPI EXAMPLE Set 1-2-3-4-5-6-7-8*-9-10-11-12-13-14-15 Grams 16.6 16.8 ----------- 17.6
(b)
17.8
Starting with set No. 2 remove every other set and with these sets make a second row keeping sets in order of descending weights. STEP II EXAMPLE Rowl 1-3-5-7-9-11-13-15 Row II 14-12-10-8*-6-4-2 *3 blade set wíthin 0.2 gram of each other.
(c)
Reposition row II to the nght of row I to form a single row of blade sets that are in assembly order. Final Row 1-3-5-7-9-11-13-15-14-12-10-8*-6-4-2 *3 blade set within 0.2 gram of each other.
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IlOílCyi/Vdl
CAUTIQN:
(d) (2)
Assemble blades into disc as shown. (See Figure 212.)
Using pin installer LTCT256, install new pins (color coded elther red or green), i( required. NOTE:
(3)
IF FOR ANY REASON A BLADE MUSI BE REPLACED, REPLACEMENT MUST BE ACCOMPLISHED USING A MATCHED SET; USING ONE BLADE OF A SET TO REPLACE THE DAMAGED BLADE AND THE OTHER BLADE OF THE SET TO REPLACE A BLADE ONE PLACE FARTHER, IN THE DIRECTION OF ROTATION, THAN THE THEORETICAL 180 DEGREES OPPOSITE BLADE.
When Installing blades, press íhumb against blade root untíl blade is seated against pin. If blades cannot be installed by hand, use installing tool LTCT4179 and torque wrench. Installation forcé should not exceed 30 inch-pounds torque.
Instan locking píate 1-100-505-02 on pin in root of disc. CAUTIQN:
DO NOT ALLOW TOOL TO CONTACT COMPRESSOR DISC AREA.
(4)
Using a soft faced mallet and a suitable brass or nylon drlft, bend tab of looking píate agamst blade root.
(5)
Perlorm the following steps for blade installation oí the second through fifth stage of the compressor rotor subassembiy. NOTE:
Blade sets for each stage are to be selected from random order. No systematic grouping is required.
CAUTIQN:
IF, FOR ANY REASON. A BLADE MUST BE REPLACED, THtS REPLACEMENT MUST BE ACCOMPLISHED USING MATCHED BLADE SETS.
(6)
Assemble blade sets for each stage into proper disc so that each blade in a set is 180 degrees from its mate.
(7)
Using pin installer LTCT256, install new pins (color coded either red or green), if required. NOTE:
(8)
When installing blades. press thumb against blade root until blade is seated against pin. If blades cannot be installed by hand, use installing tool LTCT4179 and torque wrench. Installation forcé should not exceed 30 inch-pounds torque.
install locking píate 1-100-505-02 on pin in root of disc.
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INDEX MARKS
First Stage Disc Blade Arrangement Figure 212
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HoneyweII ‘^A,NTENANCEMANUAL CAÜTION: (9)
DO NOT ALLOW TOOL TO CONTACT COMPRESSOR DISC AREA.
Using a soft faced mailet and a suitable brass or nylon drift, bend lab of locking píate against blade root.
(10)
Check compressor rotor blade tip clearances. (See Paragraph l.D.(1)(a}.)
(11)
Instan compressor and Impeller housings. (See 72-30-01.)
E. Repair Ceniriíugai Compressor (mpeller Blades NOTE: Repairs shall be made wlth small diesinker type files and India or carborundum stones. Abrasivo crocos cloth (72-00-00, 13, Table 203) shall be used for final polishing. Power tools shall not be used. All repairs shall be made by removing oniy as much material as necessary to permit a smooth repair. Minor dents and nicks in noncritical areas should not be reworked provided 0-025 inch blade thickness remains. Repair in critical area is not allowed except as shown. (See Figure 213.) NOTE:
(1)
One blade leading edge may be repaired by removing up to 0.130 inch of material. Should more than one blade require 0.075 to 0.130 inch of material removal, proceed as outlined in following step (2). NOTE:
(2)
A vibration check (see 71 -00-00) of engine must be made if steps (1) or (2) have been accomplished.
If more than five blades are atfected, forward engine to Overhaul facility for replacement of centhfugal compressor impeller assembiy.
Up to five blades requiring removal of 0.075 to 0.130 inch of material may be repaired as follows: NOTE:
(3)
The 10 total blades inelude any blades previously repaired to the 0.130 inch limit. Total of 10 blades is defined as total number of reworked blades on the impeller assembly.
(a)
Blend repair leading edge of blade (see Figure 209) using care not to exceed 0.130 inch of material removal.
(b)
Remove same amount of material from blade 180 degrees away (directly across assembly) from repaired blade.
All other repairs to impeller blades shall be accomplished in accordance with limits shown. (See Figure 213.)
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HoneyweII -.«EMAMUA. COMBUSTOR TURBINE ASSEMBLY - MAINTENANCE PRACTICES 1. Removal/Installation Comfaustor Turbina Assemblv A. Remove Combustor Turbine Assembly NOTE: The combustor turbine assembly may be removed while the engme is installed in the aircraft. (1)
Remove damps that secure ignition coil and iead assembly to combustor turbine assembly. Disconnect ignition coil and lead assembly from four igniter plugs and oil pressure and scavenge hoses.
(2)
Remove damps that secure main fuel hose assembly to combustor turbme assembly. Remove bolt and nuts that secure fuel solenoid valve to combustor turbine. Disconnect mam fuel hose assembly from fuel control and flow divider assembly. Remove hose assembly. Cap all open ports.
(3)
Remove damps that secure starting fuel hose assembly to combustor turbine assembly. Disconnect starting fuel hose assembly from starting fuel solenoid valve and tee between halves of starting fue) manifolds.
(4)
Remove bolt (12, Figure 201) and tablock (11} that secure exhaust diffuser cover (10) to rear cover (8). Remove exhaust diffuser cover (10).
(5)
Using suitable tapered feeler gages, measure gap between rear beanng cover (8) and exhaust diffuser in eight equally spaced places. The optimum gap would be 0.005 inch at all locations, but up to 0-007 inch is allowable at any point if the direct opposite measurement does not exceed 0.003 inch. !f limit is exceeded, proceed as follows: (a)
inspect ID of exhaust diffuser. If average diameter in eight places exceeds 6.066 inches, remove and replace exhaust diffuser.
(b)
Inspect OD of rear beanng cover. If average diameter in eight places is less than 6.056 inches, replace cover.
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aoic 6ti ■
©> -J Combustor Turbine Assembly Figure 201
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TRAILING EDGE REPAIR DEPTH 0 050 IN. MAX.
RADIUSASSHOWN. DOTTEDLINE INDICATESBLENDINQ. BLENDSURFACE SIMILARTO UNAFFECTED BLADE. T53L7O3144R0
Centrifugal Compressor Impeller BlacJe Repair Limits Figure 213
"70
— oO —
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MAINTENANCE MANUAL T53-L-703
KEY TO FIGURE 201 1. 2. 3. 4. 5. 6,
NUT BOLT COMBUSTOR TURBINE ASSEMBLY SHIM POWER SHAFT BOLT NUT
7. SEAL 8. REAR BEARING COVER 9. BOLT 10. EXHAUST DIFFUSER 11. COVER TABLOCK 12. BOLT
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(6)
Remove bolts (9) that secure rear cover (8) to exhaust ditfuser.
(7)
Instan three 1/4-28 threaded pusher screws in rear cover (8) at approximately 1,4 and 9 o'clock positions. Tighten screws evenly and remove rear bearing cover (8) and seal (7).
(8)
Straighten deformad rim of power shaft internal wrenching nut (6) at four places.
(9)
Instan torque adjustment fixture LTCT962 inio rear of combusíor turbina assembly and engage tangs of locking píate assembly with slots in beanng retainer nut. Secure píate assembly with three bolts.
(10)
Using Socket wrench LTCT505, remove and retaín internaí wrenching nut (6) for reuse in foKowing step (20). (See Figure 202.)
(11)
Using Socket wrench LTCT506, remove power shaft bolt (5, Figure 201) and shims (4).
(12)
Record shim thickness and attach shims, nut, and bolt to air diffuser.
(13)
Position combustión lifting sling LTCT14668-01 or equivalent, around flange of ditfuser support cone. (See Figure 203.)
(14)
Attach suitable hoist to lifting eye of adapten
(15)
Mark relationship of combustor turbine assembly to air diffuser using approved marker (72-00-00, 47. Table 203).
(16)
Using Socket wrench LTCT393, remove bolts (2, Figure 201) and nuts (1) that secure combustor turbine assembly (3) to diffuser housing.
(17)
Using an approved marking pencil, identify and mark all bolt holes at which brackets were secured. CAUTIQN:
NOTE:
(18)
WHILE REMOVING COMBUSTOR TURBINE ASSEMBLY, INSURE THE POWER SHAFT DOES NOT MOVE AFT, MOVEMENT OF THE POWER SHAFT COULD CAUSE THE SUN GEARSHAFT TO IMPACT AND DAMAGE THE TACH DRIVE SPUR GEAR.
Marking is required for proper reinstallation of same combustor turbine assembly. Do not rotate engine, combustor turbine assembly or power turbine until marking is accomplished.
Remove combustor turbine assembly sutficiently to mark relationship of power shaft to power turbine shaft using approved marker.
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Removing Power Shaft Intemal Wrenching Nut Figure 202
72 “ 40 * 00 r
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MAINTENANCE MANUAL T53-L-703
X 7JS 21 Je
Removing Combustor Turbine Assembly Figure 203
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Honeywell —^ANCEMANUAL (19)
Lower the combustor turbine assembly and place il on a suitabie work surtace. NOTE:
The original power shaft bolt flange depth must be measured and recorded for reference during reassembiy. Ftange depth measurement governs size or number of shims (4) placed under head ot power shaft bolt (5) to lócate power shaft within engine correctiy.
(20)
Instan original shims (4), power shaft bolt (5) and internal wrenching nut (6). Tighten nut snugly, using socket wrench LTCT505. Remove torque adjustment fixture LTCT962. Position exhaust diffuser down and place locating bution bar LTCT153 on combustor flange and install measuring tool 1X016124 (replaces LTCT3039) in power turbine splines.
(21)
With vernier depth gage. measure from lop of bar to top of measuring tool. (See Dimensión A, Figure 204.)
(22)
Subtract distance from top of locating bar to top of flange (Dimensión B from Dimensión A). Resulting dimensión, plus length of tool (Dimensión C), is the flange depth. Record and retain this measurement for reference during assembiy.
(23)
Install torque adjustment fixture LTCT962.
(24)
Remqve internal wrenching nut (6, Figure 201), bolt (5) and shims (4). Attach shims to bolt with lockwtre.
(25)
Remove torque adjustment fixture.
(26)
Deleted.
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Measuring Power Shaft Bott Flange Depth Figure 204
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HoneyweII MA,NTENANCE^MANUAL Figure 205. Deleled Figure 206. Deleted NOTE:
B.
Figure 207. Deleted Perform an engine vibralion test upon reinstallation of combustor turbine assembly (hot end) or whenever excessive engine vibration is suspected. {See 71-00-00, paragraph 11.E.)
Install Combustor Turbine Assembly NOTE:
Lubrication of power shaft bolt and instailation of shims is not necessary at this time.
(1)
Install power shaft bolt (5, Figure 201) into power shaft. FInger tighten to check for cleanliness and condition of threads. )f any íightness or failure of shoulder to bottom on power shaft exists, olean or repair threads. Clean mating spiines of power turbine and power shaft. Do not lubricate.
(2)
If combustor turbine assembly or major subassembly has Peen replaced, it is necessary to establish a new power shaft bolt flange depth. Compare original and new flange depth measurements (see paragraph 1 .A.(22) through (25)). If they differ by more than 0.010 mch, add or remove shims lo maintain original flange depth measurement. (See Figure 204.) A máximum of three shims may be installed. (If original measurements cannot be determined, see Figure 204, paragraph l.C.)
(3)
Establish clearance between second stage gas producer cylinder and first stage power turbine nozzle. (See Dimensión B. Figure 9.) (See 80-00-04.) NOTE:
(4)
Position mating marks as recordad when combustor turbine was removed. If mating marks were not made at removal, or if a new combustor section or a new power turbine rotor is installed, accomplish following steps (5) and (6). NOTE:
(5)
If a new combustor section or a new power turbine rotor is installed, position mating marks in steps (5) and (6) 180 degrees apart during instailation,
Check position of mating mark center punchad on face of male spiine of power shaft. Using an approved marker, mark position on outside diameter of power shaft spiine. NOTE:
(6)
If punch marks do not exist on power shaft and/or power turbine rotor shaft spIines, the power shaft may be installed tn any position relativo to the power turbine rotor shaft spiines.
Overhauted power turbine rotor may have spiines center punched two or more times, dependíng on the number of times the rotor has been rebladed- Use the mating mark with the greatest number of center punch marks.
Check position of mating mark center punched on face of female spiine on second stage power turbine rotor. If not accomplished during assembly. mark position on outside diameter of shaft using an approved marker.
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HoneyweII MAINTENANCE^MANUAL (7)
Center afl end of power shaft within the compressor shatt. CAUTION: MAKE SURE THAT TABS ON FIRST STAGE GAS PRODUCER NOZZLE LINER ARE PROPERLY ENGAGED BY THE CHANNEL ON THE COMBUSTION CHAMBER LINER. NOTE:
(8)
|{ installing combustor turbina assembly whiie engine is in vertical position, position litting eye of adapter to boles nearest attaching points of adapter.
Position combustor lifting sling LTCT14668-01 around flange of diffuser support cone. (See Figure 203)
(9} Attach suitable hoist to tiftmg eye of adapter and install combustor turbine assembly on diffuser housing assembly with combustión chamber drain valve located at 6 o’clock position. (a)
(10)
Before installalion, inspect as follows; Dimples on ID of combustión chamber imer must contact OD of first stage gas producer nozzie deflector. This may be accomplished by appiying iron blue pigment (72- 00 -00, 54, Table 203) to the liner dimples and mating the nozzie and liner to simúlate hot end installation. If contact is not evident through 360 degrees, carefully bend liner tab(s) inward as required.
Using Socket vi/rench LTCT393. install bolts (2, Figure 201) and nuts (1) that secure combustor turbine assembly (3) to diffuser housing. CAUTION:
(11)
WHEN INSTALLING COMBUSTOR TURBINE ASSEMBLY, THE POSStBILlTY OF GEAR (N2 ORIVE) TRAIN DISENGAGEMENT EXISTS WHEN POWER SHAFT IS PUSHED FORWARD. FOLLOW PROCEDURES VERY CAREFULLY
Install all brackets at areas where indicated during removal.
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MAINTENANCE MANUAL
noriGywVdi CAUTIQN:
T53-L-703
NUMBER OF SHIMS SHALL NOT EXCEED THREE. USEOFAN EXCESSIVE NUMBER OF SHIMS CAN RESULT IN A co*ckED BOLT AND CAUSE EXCESSIVE POWER TURBINE VIBRATION. MAKE SURE SHIMS ARE FLAT AGAINST SHOULDER WITHIN ROTOR SHAFT BEFORE INSTALLING POWER SHAFT BOLT SHIMS MUST BE HELD IN PLACE WITH SHORTENING COMPOUND OR ASSEMBLY FLUID (TABLE 1102 #179, IF ENGINE IS HORIZONTAL.
(12)
Instan shims (4) oí thickness recorded during removal or as corrected in the preceding steps (1) and (2).
(13)
Remove N2 tachometer (if instalied) from overspeed governor and tachometer drive gearbox and engage 1/4 inch drive extensión and handle in tachometer dríve gear. CAUTIQN:
(14)
FAILURE TO MAKE SURE ENGAGEMENT MAY RESULT IN DAMAGE TO DRlVEN GEAR. A FIRM RESISTANCE MUST BE FELTAT HANDLE.
Apply light coating of anti seize compound (72-00-00, 15. Table 203) to threads of power shaft bolt (5) and install bolt by hand. While installing bolt, roíate the 1/4 inch drive handle slightiy to make sure that the driven (N2 dríve) gear and the spur gear are engaged properiy. CAUTIQN:
MAKE SURE BOLT AND SHAFT THREADS ARE CLEAN. MAKE SURE BOLT HAS TURNED AT LEAST SIX TURNS BY HAND PRIOR TO TORQUING.
(15)
Instan torque adjustment fixture LTCT962 into rear of combustor turbine assembly and engage tangs of locking píate assembly with slots in bearing retainer nut. Secure píate assembly with three bolts.
(16)
Using socket wrench LTCT506, tighten power shaft bolt 195 to 200 inch pounds torque.
(17)
Apply light coating of antiseize compound (72-00-00, 15, Table 203) to threads of a new nut (6) and power turbine rotor shaft.
(18)
Using socket wrench LTCT505, install new nut (6). Tighten nut to 100 foot pounds torque. Loosen and remove nut. Retighten power shaft bolt 195 to 200 inch pounds torque. Install nut (6) and tighten to 50 foot pounds torque. Remove torque fixture LTCT962.
(19)
Using end of suitably rounded punch or the side of a tapered drift punch, deform collar of nut to extend into three slots of power turbine rotor shaft.
72-40-00 seS
HoneyweII M™TEM™ANUAL (20)
Visually inspect nut for cracks that may have occurred as result of deformations. It nut is cracked, it must be replaced. Remove torque adjustment fi>cture. NOTE:
Before installing seal (7), the sea! shall be inspected for cuts, nicks, tears, cracks, distortion, pliability and wear. If damage is noted, replace seal. Make sure groove in rear bearing cover (8) is deán. Coat groove in rear cover with shortening compound (72-00-00, 38, Table 203) or assembly fluid (72-00-00, 7, Table 203) to facilítate hoiding seal during assembly.
(21)
Instan seal (7) or packing in groove of rear cover (8).
(22)
Prior to installing the rear bearing cover (8), inspect screw (21, Figure 209) to make sure screw head does not protrude. Take correctiva action if screw head does protrude. NOTE:
Prior to installation of bolts (9), apply a light coat of antiseize compound (72-00-00, 15, Table 203) to threads of bolt.
(23)
Instan rear bearing cover (8) and secure with botts (9). Torque 70 to 95 inch-pounds and lockwire (72-00-00, 40, Table 203).
(24)
Using suitable tapered feeler gage, measure gap between rear bearing cover (8) and exhaust diffuser in eight equally spaced places. The optimum gap would be 0.005 inch on all eight locations, but up to 0.007 inch allowable at any point if the direct opposite measurement does not exceed 0.003 inch. If limit is exceeded, proceed as follows; (a)
Inspect ID of exhaust diffuser. if average diameter in eight places exceeds 6.066 inches, remove and replace exhaust diffuser.
(b)
Inspect OD of rear cover. If average diameter in eight places is less than 6.056 inches, replace rear cover.
CAUTION:
NOTE:
SHORT TAB MUST GO THROUGH HOLE IN EXHAUST DIFFUSER COVER AND INTO CUTOUT IN REAR COVER. MAKE SURE TAB RÉMAINS ENGAGED IN BOTH COVERS AFTER TIGHTENING BOLT.
Prior to installation of bolt (12) apply a light coat of antiseize compound (72-00-00, 15. Table 203).
(25)
Position exhaust diffuser cover (10) over rear bearing cover (8) and align tablock holes. Secure exhaust diffuser cover (10) with tablock (11) and bolt (12). Tighten bolt as required and lockwire bolt to tablock.
(26)
If N2 tachometer was removed, lubrícate spiines with spiine lubricant (72-00-00, 45, Table 203) and install.
(27)
Apply light coat of thread lubricant (72-00-00, 15, Table 203) to the igniter plugs.
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Honeyi/vell MAINTENANCE^MANUAL {28) Instan tour starting fuel nozzles and four igniter plugs. Tighten igniter plugs 85 to 95 inchpounds torque. (29)
Reconnect ignition leads, main fuel hose assembly, fuel solenoid valve and starting fuel hose assembiy. Secure with clamps as necessary.
NOTE:
Perform the following procedure if original flange depth measurements have been lost. flange shims have been lost or major assemblies in combustor turbina assembly have been replaced. Combustor turbine (hot end) must be installed on the engine.
C.
Power Shaft Bolt Flange Depth Measurement (1)
If installed, remove power shaft bolt (5, Figure 201) and locating shim (4). CAUTION:
IF POWER SHAFT IS NOT IN EXTREME FORWARD POSITION ENGINE FAILURE CAN RESULT.
(2)
Using a deán rod (wood or phenolic dowel), gently but firmiy push power shaft to extreme forward position.
(3)
Place locating button bar LTCT153 across back of exhaust diffuser and note dimensión from bar to aft end of power shaft. This is Dimensión A. {See Figure 208.)
(4)
With bar in the same position, note dimensión from bar to power shaft bolt seating shoulder in second stage power turbine rotor assembly. This is Dimensión B.
(5)
Subtract Dimensión B from Dimensión A to obtain Dimensión C.
(6)
Subtract 0.230 inch from Dimensión C to obtain Dimensión D.
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MAINTENANCE MANUAL T53-L-703
Measuring Power Shaft Bolt Flange Depth Figure 208
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HoneyweII MAINTENANCE^MANUAL
2.
(7)
Subtract Dimensión D from the power shaft bolt length (5.400 inches) to obtain the required thickness oí shim.
(8)
Install shims of corred thickness and bolt. (See steps 1.B(9) through (26).)
Disassembiv/Reassemblv Combustor Turbine Assemblv A.
Disassemble Combustor Turbine Assembly (See Figure 209.) (1)
Remove V-band coupling assembly (7 or 7A) by one of the following methods. (a)
For V-band assembly (7), disconnect nuts (1) from bolts (3) and remove spacers (2, 4).
(b)
For V-band assembly (7A), disconnect nuts (1A) from bolts {3A).
(2)
Remove two screws (39, 40) and nuts (41) from connector (38). Open connector and remove lead of thermocouple harneas (42).
(3)
Remove diffuser support cone assembly (8). Remove connector (38).
(4)
Remove oil stralner housing adapter (9) from power turbine olí tube (20) at top of fire shieid (19) . Remove packing (11) and strainer (10).
(5)
Remove connector (12) from tube (20) at bottom of fire shieid (19). Remove packing (13). CAUTION- USE CARE WHEN REMOVING MANIFOLD TO PREVENT DAMAGE TO FUEL NOZZLES.
(6)
Remove start fuel nozzles. (See 73-10-03.)
(7)
Remove bolts (14) that secure fuel manifolds (18) to rear of combustión chamber assembly (59). Carefully remove manifolds from combustión chamber housing and remove seáis (15) from fuel nozzles. Remove screw (16) that secures sealing gasket (17) to main fuel manifold. Remove gaskets. Cap open parts and package or set in dust free area. If manifold is to be replaced, endose manifold in barrier material (72-00-00, 9, Table 203) or in a transparent flexible bag (72-00-00, 8, Table 203) and secure in reusable container. The container shouid be enclosed ín a waterproof cardboard box and identified for shipment.
(8)
Remove two screws (44) that secure cover assembly (43) lo fire shieid (19). Remove cover assembly from fire shieid and from lead of thermocouple harness (42).
(9)
Remove fire shieid (19) from around exhaust diffuser (22).
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Combustor Turbine Assembly Figure 209
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HoneyweII
MAINTENANCE MANUAL T53-L-703
KEY TO FIGURE 209 1. 1A. 2. 3. 3A. 4. 5.
NUT NUT SPACER BOLT BOLT SPACER V-BAND TRUNNION
6. 7. 7A. 8. 9. 10. 11. 12. 13. 14. 15. 16. 17. 18. 19. 20. 21. 22, 23, 24. 25. 26. 27.
END, LOOP V-BAND ASSEMBLY V-BAND ASSEMBLY CONE ASSEMBLY ADAPTER OIL STRAINER PACKING CONNECTOR PACKING BOLT SEAL SCREW GASKET MANtFOLD ASSEMBLY FIRE SHIELD POWER TURBINE OIL TUBE SCREW DIFFUSER ASSEMBLY NUT PIN STUD PLATE DIFFUSER NUT SEAL
28. 29.
30. 31. 32. 33. 34. 35. 36. 37. 38. 39. 40. 41. 42. 43. 44. 45. 46. 47. 48. 48 A. 49. 50. 51. 52. 53. 54. 55, 56. 57. 58. 59.
TURBINE ROTOR AND BEARING HOUSING PACKING BOLT LOCKING PLATE LOCKING PLATE BOLT BOLT MOUNTING PLATE CONNECTOR SCREW SCREW NUT HARNESS ASSEMBLY COVER ASSEMBLY SCREW FIRST TURBINE NOZZLE BOLT LOCKING PLATE SEALING FLANGE FIRST STAGE POWER TURBINE ROTOR PIN BLADE BLADE FIRST STAGE POWER TURBINE DISC SPACER PIN SPACER SECOND TURBINE NOZZLE RING SPACER COMBUSTION CHAMBER ASSEMBLY
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Honeyweil ^««NTE^MNCE^MANUAL (10 )
(11)
Rernove two power turbíne oil tubes (20) from exhaust diffuser struts. Turn combustor assembly over, set it on the aft llange of the exhaust diffuser and straighten locking plates (33, 34) and rernove 20 bolts (32). Rernove locking plates. CAUTIQN: USE CARE WHEN REMOViNG THERMOCOUPLE HARNESS FROM FLANGES TO AVOID DAMAGING ELECTRICAL CONTACTS.
(12 )
Cut lockwire and rernove two bolts (35) securing thermocoupie harness (42) to flanges of first stage power turbine nozzle assembly (45) and exhaust diffuser (22),
(13)
Rernove first stage power turbine nozzle from power turbine rotor and rernove spacer (55). Record thickness of spacer for reassembiy.
(14)
If thermocoupie harness or nozzle is to be replaced, cut lockwire and rernove 12 bolts (36) and plates (37) securing thermocoupie harness probes to first stage power turbine nozzle assembly (45). Carefully withdraw probes from nozzle and rernove thermocoupie harness (42). NQTE: Be sure to matchmark all rotating components, induding bolts (46), with white opaque ink (72-00-00, Table 203, item 73A) to make sure that they are reinsfalled in same location.
(15)
Straighten tabs of locktng plates (47); then rernove bolts (46) and locking plates (47).
(16)
Rernove seallng flange (48) from face of first stage power turbine rotor assembly (48A).
(17)
Using mechanical puller LTCT4682 (detall of LTCT46S0) extended and hooks counterdockwlse as viewed from handle end, rernove first stage power turbine rotor (52) and spacer (53) as a unit. Rernove packing (31).
(18)
Remove pins (54) and spacer (55). Record thickness,
(19)
Turn rotor and spacer over and, using puller LTCT4680, with arms retracted and hooks clockwise. rernove spacer (53) from turbine rotor (52).
(20)
Rernove second stage power turbine nozzle (56), ring (57) and spacer (58). Record thickness of spacer for reassembiy.
(21)
Sepárate combustión chamber assembly (59) from exhaust diffuser assembly (22).
(22)
(23)
(24)
(25)
Position exhaust diffuser, with second stage power turbine rotor assembly down, in holding fixture LTCT4553. Rernove screws (21) that secure power turbine rotor and bearing housing assembly (30) to exhaust diffuser (22). Raise assembly slightly from hotdmg fixture. Using mechanical puller LTCT4700, sepárate turbine rotor assembly from exhaust diffuser. Rernove and discard seal (29).
72-40-00
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HoneyweII B.
Reassemble Combustor Turbina Assembly NOTE:
Inspect power turbina rotor spiined shaft Jor canter punch. This mark will coincide with yellow "H" on disc face indicating the heavy point. If punch mark is not evident, mark position on outside diameter of spiined shaft using an approved marker. Make sure groove in housing is olean. If packing (31) is to be installed. coat groove with shortening compound (72-00-00, 38, Tabíe 203} or assembly fluid (72-00-00, 7, Table 203) to facilitate holding seal in groove during assembly.
(1)
Place power turbine rotor and bearing housing assembly (30, Figure 209) forward face down into holding fixture LTCT4553. Install packing (31) in groove on aft end of bearing housing.
(2)
Place exhaust diffuser assembly (22) over bearing housing and align screw holes.
(3)
Temporarily install 1/4-28 bolts and fíat washers through exhaust diffuser assembly and into bearing housing. Turn bolts evenly and pulí exhaust diffuser over bearing housing.
(4)
Secure bearing housing to exhaust diffuser with screws (21). Tighten screws 20 to 30 inch pounds torque.
(5)
Using bent 0.070 inch diameter wire, check for 0.070 inch minimum clearance between second stage power turbine rotor and forward face of inner diffuser cone. NOTE:
if installed, combustión chamber iiner should be removed to facilitate reassembiy. (See 72-40-03.)
(6)
Position exhaust diffuser and bearing housing on bench with exhaust diffuser rear face down. Position combustión chamber assembly (59) on flange of exhaust diffuser and align matchmarks on mating flanges.
(7)
Establish tip clearance between second stage power turbine rotor and second stage power turbine nozzle (see paragraph 2.D.). Check axial clearance between second stage power turbine nozzle and rotor. CAUTION:
MAKE SURE THAT BOLTS DO NOT BOTTOM AGAINST SEAL HOUSING.
(8)
Install power turbine spacer (53) over end of power turbine rotor and align bolt holes and matchmarks that were printed at disassembiy. Secure spacer with three equally spaced 5/16-24 bolts and washers.
(9)
Position second stage power turbine nozzle (56) and using feeler gage, check clearance between power turbine spacer (53) and second stage power turbine nozzle (56). If clearance is less than 0.005 inch, rework nozzle using half round file to obtain 0.010 inch clearance.
(10)
Establish clearance between first stage power turbine rotor and second stage power turbine nozzle ustng wire gages as follows; (a)
Remove bolts and washers installed in preceding step (3).
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HoneyweII MA,NTENAN«MANUAL (b)
Instail tonque adjustment fixture LTCT962 into rear of exhaust ditfuser assembly and engage tangs of (ocking píate assembíy with slots in beanng retainer nut. Secure piafe assembly with three bolts. Replace combustor turbine assembly on bench with exhaust ditfuser rear face down.
(c)
Instail packing (31) over end of power turbine rotor shatt.
(d)
Position first stage power turbine rotor (48A. Figure 209) over end oí power turbine rotor shaft. Lócate yellow “H" on disc face. 180 degrees from punch mark (or other mark) on power turbine shaft. Align bolt holes. NOTE:
Prior to installation, apply antiseize compound (72-00-00, 15, Table 203) to bolts (46). Make sure that locking piafes do not cover the three small air bleed holes in the sealing flange.
(11)
(e)
Secure rotor with sealing flange (48), locking platas (47) and bolts (46). Tighten bolts 140 to 160 inch pounds torque. Do not bend locking píate tabs at this time. Remove torque ad/ustmení fixture LTCJ962.
(f)
Using wire gage LTCT14807 measure between first power turbine aft blade root and second power turbine forward nozzle inner shroud. Clearance shall be 0.065 to 0.130 inch.
(g)
Using wire gage LTCT14807 measure between first power turbine blade tip and second power turbine nozzle outer shroud. Clearance shall be 0.062 to 0.077 inch.
(h)
If clearances in steps (f) and (g) are not within limits, remove first power turbine wheel (see 72-40-00, paragraph 2.A.(17)). Seleot approphate spacer (58) from Table 201. When this spacer is changed second stage power turbine rotor tip and axial clearances must be rechecked. (See paragraph 2.D.)
Altérnate to (8A): Establish clearance between first stage power turbme rotor and seoond stage power turbine nozzle (see Dimensión G, Figure 210) as follows: (a)
Plaoe locating button bar LTCT153 on flange of combustión chamber housing.
(b)
Using a vernier depth gage, measure from bar to outer shroud of second power turbine nozzle (Dimensión A).
(c)
Using a vernier depth gage, measure from bar to power turbine spacer (53, Figure 209). (See Dimensión B, Figure 210.)
(d)
Subtract Dimensión B from Dimensión A. Result is Dimensión C.
(e)
Place first stage power turbine rotor (48A, Figure 209) on bench with forward face down. Position locating button bar LTCT153 on blade disc.
(f)
Using a vernier depth gage, measure from bar to spacer surface. (See Dimensión D, Figure 210.)
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HoneyweII
MAINTENANCE MANUAL T53-L-703
XA-73S*J39
Determining Clearance Between First Stage Power Turbine Rotor Assembly and Second Stage Power Turbine Nozzle Assembly Figure 210
72-40-00
Page 221 Sepl 30/02
HoneyweII MA,NT„MANUAL (g)
Using a vernier depth gage, measure from bar to shrouded tip of highest blade (Dimensión E).
(h)
Subtract Dimensión E from Dimensión D. Result is Dimensión F.
(i)
Subtract Dimensión F from Dimensión C. Result is Dimensión G.
(j)
Dimensión G musí be within 0.062 inch mínimum to 0.077 inch máximum. If desired Dimensión is not obtained, spacer is required to position second stage power turbine nozzle. NOTE:
Spacer is selected in paragraph 2-D. Refer to that size before replacing spacer. Shimming of the second stage power turbine nozzle will affect the axial clearance between the second stage power turbine nozzle and the first stage power turbine wheel, the axiaí clearance between the second power turbine rotor and second power turbine nozzle, and second power turbine rotor tip clearance.
(k)
Select and instan necessary spacer (58, Figure 209). (See Table 201.). Instan ring (57). second stage power turbine nozzle (56) and temporarily secure with four 1/4 x 28 UNF bolts in same position from which removed and pins (54). Space bolts equally. Jorque as required. Table 201. Spacer Thickness Parí Number
Thickness
1-140-303-T)1
0.022 to 0.028 inch
1-140-303-02
0-029 lo 0.035 inch
1-140-303-03
0.036 to 0.044 inch
(12)
Remove bolts and washers installed in preceding step (3).
(13)
Instan torque adjustment fixture LTCT962 into rear of exhaust diffuser assembly and engage tangs of locking píate assembly with slots m bearing retainer nut. Secure píate assembly with three bolts. Replace combustor turbine assembly on bench with exhaust diffuser rear face down.
(14)
Instan packing (31) over end of power turbine rotor shaft.
72-40-00 sS
HoneyweII “,NTE.ANCE^MANUAL (15)
Position (irst stage power turbina rotor (48A, Figure 209) over end of power turbine rotor shaft. Lócate yellow “H" on dtsc face, 180 degrees from punch mark (or other mark) on power turbine shaft. Align bolt holes. NOTE; Prior to msta/lation, apply arttiseize compound (72-00-00, 15, Table 203) to bolts (46). Make sure Ihaf (ocking plates do not cover ttie three small air bleed holes in the sealing flange. To instan first stage power turbine nozzle, checking axial clearances using wire gages LTCT14807, see step (26).
(16)
Secure rotor with sealing flange (48). locking plates (47) and bolts (46). Tighten bolts 140 to 160 inch pounds torque. Do not bend locking píate tabs at this time. Remove torque aOjustment fixture LTCT962.
(17)
Establish clearance between first stage power turbine nozzle and shrouded tip of first stage power turbine rotor blades (see Dimensión D. Figure 211) as follows: (a)
Place locating button bar LTCT153 on flange of combustión chamber housing.
(b)
Using a vernier deptfi gage, measure from bar to ring (57, Figure 209) installed on combustión housing flange. (See Dimensión A. Figure 211,)
(c)
Using a vernier depfh gage, measure from bar to shrouded tip of highest first stage power turbine blades (Dimensión B).
(d)
Subtract Dimensión B from Dimensión A. Resulí is Dimensión C.
(e)
Place first stage power turbine nozzle (45, Figure 209) on bench with forward face down. Position locating button bar LTCT153 on aft flange of nozzle.
(f)
Using a vernier depth gage, measure from bar to outer shroud. (See Dimensión E, Figure 211.)
(g)
Subtract thickness of locating bar from Dimensión E.
(h)
Subtract Dimensión C from dimensión arrived at in precedíng step (g). Resulf ís Dimensión D.
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HoneyweII
MAINTENANCE MANUAL T53-L-703
Determining Clearance Between First Stage Power Turbine Nozzle and í%?tor Assemblies Figure 211
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Page 224 Sepl 30/02
HoneyweII ^AINT^MANUAL (i)
(18)
Dimensión D must be within 0.063 inch mínimum lo 0.078 inch máximum. (í desired dimensión is not obtained, spacer is required lo position first stage power turbme nozzle. Selecí necessafy space: (55. Figure209). (SeeTable 201.)
Establish tip clearance between first stage power turbine rotor and first stage power turbme nozzle. (See paragraph. 2.C.) NOTE:
Bolts (32) may not extend through retaining nuts on exhaust diffuser.
(19)
Position spacer (55, Figure 209), selected in preceding step (15), ring (57). Iristall four equally spaced bolts (32) through spacer (55), ring (57) and into exhaust diffuser.
(20)
Position combustor turbine assembly at 45 degree angle and support it in this position.
(21)
Position dial mdioator against a point just inboard of first stage power turbine blade roots. Roíate power turbine assembly and record runout. Runout must be within 0.004 inch TIR. Record runout.
(22)
If runout is not within limits, loosen and re-torque bolts (46).
(23)
Reposition combustor turbine assembly on bench.
(24)
Bend locking píate (47) tabs against bolts (46).
(25)
Make sure that proper spacer (55), selected in preceding step (15) is installed. Remove bolts (32) installed in step (17).
(26)
Instan first stage power turbine nozzle as follows: (a)
Position combustor turbine assembíy at 45 degree angle and support it in this position.
(b)
Position dial indicator against a point just inboard of first stage power turbine blade roots. Rotate power turbine assembly and record runout. Runout musí be within 0.004 inch TIR. Record runout.
(c)
If runout is not within limits, loosen and re-torque bolts (46).
(d)
Reposition combustor turbine assembly on bench.
(e)
Bend locking píate (47) tabs against bolts (46).
(f)
Remove four bolts and three pins installed in step (1l)(k).
(g)
Seiect nominal size spacer (55, Figure 209, Table 201). Install spacer with three pins removed in preceding step.
(h)
Install first power turbine nozzle over first power turbine rotor into ring (57). Secure in place with four equally spaced bolts (32). Torque bolts.
(i)
Using wire gages LTCT14807, check clearance D and F (see Figure 211). Clearance shall be as folJows;
72-40-00
Page 225 Sept 30/02
HoneyweII MAÍNTENANCEMANUAL D Limits: 0.063 to 0.075 mch. F Limits: 0.095 to 0.150 inch. If clearance D and F are not within limits, select new spacer and repeat preceding. (27)
Instan first stage power turbine nozzle (45) over power turbme rotor and align bolt boles.
(28)
Apply antiseize compound (72-00-00, 15, Tabie 203) to bolts (32).
(29) (30)
Secure first stage power turbine nozzle with bolts (32) and locking plates (33, 34). Insert thermocouple harness assembly lead through exit hole in flanges of first stage power turbine nozzle assembly (45) and exhaust diffuser (22). Secure lead to flanges with two bolts (35). Tighten, as required, and lockwire.
(31)
Pótate combustor turbine assembly to horizontal position with combustión chamber drain valve at 6 o'clock position. Using feeler gage, check clearance between first stage power turbine nozzle and seating flange. tf clearance is tess than 0.005 inch, rework nozzle using hall round file to obtain 0.015 inch minimum clearance.
(32)
Bend tabs of locking plates (33, 34) against bolts (32) and stake securely. CAUTIQN:
NOTE:
TO PREVEN! OlL LEAKS, POWER TURBINE OiL TUBES MUST SEAT PERFECTLY. IF SEATING IS STILL NOT PERFECT REPLACE TUBES AND REPEAT FOLLOWING STEP
A perfect seal will be indicated by an unbroken ring on the tapered seat of the power turbine tube. Do not lubrícate threads on power turbine oil tubes (20).
(33)
Lightiy coat tapered seats of two power turbine tubes (20) with iron blue pigment (72-00-00, 54, Table 203). Install tubes into top and bottom struts of exhaust diffuser and thread finger tight. Remove tubes and inspect seats.
(34)
If seating is imperfect, check tubes for deán connectors. Interchange tubes and repeat preceding step (33).
(35)
Tighten each power turbine oil tube to 100 to 110 inch pounds torque and lockwire.
(36)
Reinstall combustión chamber liner. (See 72-40-03.)
(37)
Position combustor turbine assembly on work bench with exhaust diffuser side up and remove bolts and washers installed in step (3).
(38)
Position fire shieid (19) on combustión chamber housing rear flange and align pin in combustión chamber housing with hole in fire shieid assembly. If oil tubes are not concentric with holes in fire shieid, remove fire shieid and file as required.
(39)
Push thermocouple harness lead through firo shieid access hole.
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Page 226 Sept 30/02
HoneyweII “"NT„MANUAL (40)
To make sure of proper alignment of combustión chamber liner with firesbieid and combustión chamber housing, position combustión chamber alignment fixture LTCT4174 through these components. Remove fixture. CAUTION:
USE CARE TO PREVENT DAMAGE TO SEALS.
(41)
Instan seáis (15) on fuel nozzles. Install sealing gasket (17) on mam fuel manifold. Carefully position two fuel manifoid assemblies (18) over fire shieid and align fuel nozzles with port holes. Install fuel manifoid assemblies and secure with boits (14). Tighten bolts as required and lockwire.
(42)
Install starting fuel nozzles. (See 73-10-03.)
(43)
Apply Molykote Type Z (72-00-00, 15, Table 203) to oil stralner housing adapter (9).
(44)
Install strainer (10) into adapter (9) at 12 o'clock position and tighten finger tight. Install oii strainer housing adapter (9) and packing (11 ¡ into oil tube. Tighten adapter 80 to 90 pound inches torque and lockwire.
(45)
Apply Molykote Type Z (72-00-00, 15, Table 203) to connector (12).
(46)
Install connector (12) and packing (13) into power turbine tube at 6 o'clock position. Tghten connector 80 to 90 inch pounds torque and lockwire.
(47)
Insert lead of thermooouple harness (42) through cover assembly (43); then install cover assembly onto fire shieid (19). Secure cover assembly with two screws (44).
(48)
Install support cone assembly (8) over fire shieid and exhaust diffuser. Position starting fueiing manifoid bracket at 12 o'clock position.
(49)
Deleted.
(50)
Deleted. NOTE:
Lead shall bottom in oonnector.
(51)
Open cover of conneotor (38) and install lead of thermocouple harness (42). NOTE: To make sure proper seating of the support cone on the combustión chamber, tap the V-band coupling assemblies starting at the middie and moving toward the bolts at the ends. Tighten the nuts. Repeat tapping and tightening until the nuts cannot be easily drawn up further.
(52)
Position V-band assembly over support cone and combustión chamber housing flange with attaching ends at approximately 4 and 10 o'clock positions as viewed from rear. Secure Vband assembly by one of the following methods. (See Figure 209.) (a)
For V-band assembly (7), secure with bolts (3), spacers (2, 4j and nuts (t).
(b)
For V-band assemblies (7A), secure with bolts {3A} and nuts (lA).
72-40-00
Page 227 Sept 30/02
HoneyweII MA,NTENANCE^MANUAL (53)
C.
Tighten V-band coupling nuts to 200 inch pounds torque. Seat clamps by tapping with a sott faced mallet. Release torque to zero inch pounds torque. Retighten 145 to 155 inch pounds torque. Make sure an equal gap, plus or minus 3/32 inch, exists between V-band coupling assembly ends. Lockwire nuts and bolts.
Establish First Stage Power Turbine Rotor Tip Clearance (1)
Using 0-020 inch copper wire and tape (72-00-00, 64, Table 203). determine actual tip clearances: (a)
Measure thickness of tape. NOTE:
(b)
Apply enough thickness of tape on bfade tips so fhat the thickness of wire plus a single layer of tape on top of the wire equals the mimmum tip clearance of 0.025 inch.
Secure short length of copper wire on tips of power turbine blades at three locations 120 degrees apart. Place one short length of wire on forward tip of blade and one on aft tip of the same blade.
(2)
Paint tape with iron blue pigment (72-00-00, 54, Table 203).
(3)
Remove four bolts (32, Figure 209) and three pins (54) installed in ring (57).
(4)
Instan spacer (55) (thickness determined in paragraph 2.B.(17)) on combustión chamber flange and align bolt holes. Install three pins (54). Pins shall be selectively fit to obtain 0.0005 to 0-01OL inch loose fit. Use three pins of same dash number. (See Table 202.) NOTE:
Use care not to rub against tape.
(5)
Carefully position first stage power turbine nozzle (45, Figure 209) over first stage power turbine rotor (7). Align bolt holes.
(6)
Secure nozzle to exhaust diffuser with four equally spaced bolts. Tighten bolts eveníy to proper torque.
(7)
Roíate power turbine rotor one revolution, using hand crank LTCT4650 fitted into spiine of second power turbine rotor. Table 202. Selective Pin Diameters Part Number
Shank Diameter
1-190-121-01
0.2495 to 0.2505
1-190-121-02
0.2510 to 0.2515
1-190-121-03
0.2520 to 0.2525
1-190-121-04
0.2530 to 0.2535
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Page 228 Sept 30/02
HoneyweII (8)
Remove bolts that secure first stage power turbina nozzle and carefully remove nozzle.
(9)
Check tape for signs of rubbing. If rubb/ng is not evident, tip clearance is accepíabie. If rubbing is noteú, proceed to step (10).
(10)
D.
MAINTENANCE MANUAL T53-L-703
If rubbing is evident, determine tip clearance as follows: (a)
Select tape from each diameter which has greatest rub.
(b)
H iron blue pigment has been removed but tape has not been cut, tip clearance is equal to diameter of wire plus total thickness of tape used at that position.
(c)
If tape has been cut completely through but wire has not been damaged, tip clearance is equaí to diameter of wire plus thickness of tape under wire.
(d)
If tape has been cut completely through and wire appears damaged, measure diameter of wire. The tip clearance is equal to mínimum wire diameter plus thickness of tape under wire.
(11)
Tip clearance determined in preceding step (10) shal! be 0.025 inch minimum. If desired clearance is not obtained, recheck alignmení and íorquing of bearing housing to exhaust diffuser or replace nozzle.
(12)
Remove all installed tapes and wires.
Establish Second Stage Power Turbine Rotor Tip Clearance NOTE: (1)
Altérnate method using wire gages is in step (8).
Using 0.020 inch copper wire and tape (72-00 - 00, 64. Table 203) determine actual tip clearance: (a)
Measure thickness of tape. NOTE:
(b)
Apply enough thicknesses of tape on blade tips so that the thickness of the wire plus a single layer of tape on top oi the wire equals the minimum tip clearance of 0.025 inch.
Secure short length of copper wire on tips of power turbine blades at three locations 120 degrees apart. Place one short length of wire on forward tip of blade and one on aft tip of the same blade.
(2)
Painí tape wiíh iron blue pigment (72-00-00, 54, Table 203).
(3)
Place spacer of 0.032 inch nominal thickness (58, Figure 209 and Table 201) and ring (57, Figure 209) on combustión chamber flange and aügn bott holes. Install three pins (54), Select pins to obtain 0.0005 to 0.001 inch loose fit. Píns shall be the same dash number. Record thickness for use in paragraph 2.B.(11)(k).
(4)
Apply antiseize compound (72-00-00, 15, Table 203) to bolts (25).
(5)
Secure ring and spacer with four equally spaced bolts (14). Tighten bolts evenly to proper torque.
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Page 229 Sept 30/02
HoneyweII NOTE:
Use care not to rub against tape.
(6)
Carefully position second stage power turbine nozzle (56) over power turbine rotor and into ring (57).
(7)
While maintaining downward pressure on nozzle rotate power turbine rotor one revolution, using hand crank LTCT4650 installed in second stage power turbine rotor.
(8)
Using wire gages LTCT14807, check axial clearance between inner shroud ot second power turbine nozzle and second power turbine rotor blade root. ümits are 0.063 to 0.153 inch. Check clearance between second power turbine blade tips and outer shroud of second power turbine nozzle. Limits are 0.060 to 0.186 inch. II limits are not met, replace spacer selected in step (3). Repeat steps (5) through (8).
(9)
Carefully remove nozzle and check tape for signs of rubbing. If rubbing is not evident, tip clearance is acceptable. If rubbing is noted, proceed to step (10).
(10)
3.
MAINTENANCE MANUAL T53-L-703
If rubbing is evident, determine tip clearance as follows: (a)
Select tape from each diameter which has greatest rub.
(b)
If iron blue pigment has been removed, but tape has not been cut, tip clearance is equal lo diameter of wire plus totai thickness of tape used at that position.
(c)
If tape has been cut completely through, but wire has not been damaged, tip clearance is equal to diameter of wire plus thickness of tape under wire.
(d)
If tape has been cut completely through and wire appears damaged, measure diameter of wire. Tip clearance is equal to mínimum wire diameter plus. Thickness of tape under the wire.
(11)
Tip clearance determmed in preceding step (10) shall be 0.025 inch mimmum. If desired clearance is not obtained, recheck aiignment and torquing of bearing housing to exhaust diffuser or replace nozzle.
(12)
Remove all installed tapes and wires.
Inspection/Chnck Combustor Turbine Assemblv A. Inspect Combustor Turbine Assembly (1)
Visually inspect the combustor turbine assembly.
(2)
Perform a power shaft bolt flange measurement. (See paragraph I.A. (18) through (20)).
(3)
Using a 0.020 inch feeler gage, perform a tip clearance of the second stage gas producen
(4)
Using a 0.025 inch diameter wire. perform a tip clearance check of the second stage power turbine rotors.
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Page 230 Sept 30/02
HoneyweII 4.
Cleanina/Paintina Combustor Turbine Assemblv A. Clean Combustor Turbine Assembly (1)
Referió SPM. 70-00-00.
72-40-00
Page 231/232 Sept 30/02
Honeywell MA,NTENAN«MANUAL V--BAND CQUPLING ASSEMBLY. QIL STRAINER HOURING ADAPTER. CONNECTOR, POWER TURBINE TUBES AND FIRF SHIELD ASSEMBLY - MAINTENANCE PRACTICES 1- Insoection/Check V-Band Couplinq Assembiv. Oil Strainer Housina Adaoter, Connector, Power Turbine Tubes and Pire Shieid Assembly A. Inspect All Parts (1)
Visually inspect threaded parts for crossed or damaged threads.
(2)
Visually inspect parís for cracks or distortion. (See Figure 201.)
(3)
Visually inspect fire shieid for cracks originafing from the lockplate areas. Límits are as follows: NOTE: Circumferential cracks appearing on both sides in forward area of lockplate indícate cracking beneath surface. These cracks shall be considered as affecting the wlOth (one side) of lockplate. (a)
Cracks extending along any two sides of either lockplate are acceptable. Cracks extending along more than two sides are not aliowed.
(b)
Cracks up to 1 inch in length are acceptable without repair provided limit of preceding step (a) is not exceeded. NOTE:
(c)
Cracks emanating from below forward area of íockplate need not be stop drilled unless visible portion is greaterthan 1 inch in length-
Cracks between 1 and 3 inches in length are acceptable provided íhey are stop drilled and limit of proceeding step (a) is not exceeded.
2. Cleanina/Painting V-Band Coupling Assembly Oil Strainer Housina Adapten Connector. Power Turbine Tubes and Fire Shieid Assembly A. Clean All Parts (1)
Clean all parts using dry cleaning solvent (72-00-00. 62, Table 203).
(2)
Clean attaching hardware using vapor degreasing method (refer to SPM, 70-15-01, SP C201) or dry cleaning solvent (72-00-00, 62, Table 203).
72-40-01
Page 20i Sept 30/02
HoneyweII ------
XA-133B 129
Pire Shieid Crack Limits Figure 201
72-40-01
Page 202 Sept 30/02
HoneyweII --«MANUAL 3- Aporoved Recairs V-Band Couolina Assemblv, Oii Strainer Housing Adaoter Connector, Power Turbine Tubes and Fire Shieid Assemblv A. Repair All Parts Refer to Repair Manual. 72-09-30 for all repairs.
TO Af\ 7 2 “ 4 0 “ ü l Sept 30/02
Page 203/204
HoneyweII ‘^A.NTENANCE^MANUAL EXHAl JST DIFFUSER SUPPORT CONE ASSEMBi Y - MAINTENANCE PRACTICES 1.
Disassembiv/Reassemblv Exhaust Diffiiser SuPDort Cone Ass^mblv NOTE:
A.
Disassemble the exhaust difíuser support cone assembly oniy as required to correct visible damage.
Disassemble Support Cone Assembly (1)
Cut and remove lockwire trom botts (3. Figure 201).
(2)
Remove bolts that secure retainers (1,2). Remove retainers. NQTE: Support assembly must be tagged and flanges indexed for support location. Supports are not interchangeable.
(3)
Remove pins (9) from support assemblies (4). Remove support assembües from flanges ( 10 .
11 ) .
(4)
Remove connector (72-40-00, 38, Figure 209).
(5)
Repeat preceding steps (1) through (3) for remaíning support assemblies (5, 6, 7. 8, Figure 201)
B.
.
Assemble Support Cone Assembly NOTE:
Refer to tags for support assembly locations.
(1)
Position support assembly (6, Figure 201) on flanges (10, 11).
(2)
Instali pins (9) into support assembly.
(3)
Position retainers (1, 2) on support assembly (4) and secure with bolts (3).
(4)
Lockwire bolts.
(5)
If removed, instali connector (72-40-00, 38, Figure 209) on bracket on difíuser support cone (8) and secure with screws (39) and (40) and nuts (41).
(6)
Connect thermocouple lead assembly (42) to connector (38).
(7)
Repeat preceding steps (1) through (3) for remaining support assemblies (5. 6, 7. 8, Figure 201)
.
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HoneyweII
MAINTENANCE MANUAL T53-L-703
Exhaust Diffuser Support Cone Assembly Figure 201
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HoneyweII KEY TO FIGURE 201 1. 2. 3. 4. 5. 6.
RETAINER RETAINER BOLT SUPPORT ASSEMBLY SUPPORT ASSEMBLY SUPPORT ASSEMBLY
7. 8. 9. 10. 11.
SUPPORT ASSEMBLY SUPPORT ASSEMBLY PIN REAR FLANGE FRONT FLANGE
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Honeyfvell MA,NTENAN™ 2.
Inspection/Check Exhaust Diffuser SuDDort Cone Assemblv A. Inspect Support Cone Assembiy (1)
Visually inspect all parts for cracks and distortion.
(2)
Inspect all threaded parts for crossed or damaged threads.
3- Cleaning/Painting Exhaust Diffuser Support Cone Assemblv A. Clean Support Cone Assembiy (1)
Clean all parts using dry cleaning solvent {72-00-00, 62, Table 203).
4. Approved Reoairs Exhaust Diffuser Supoort Cone Assemblv A. Repair Support Cone Assembiy (1)
Repair damaged threads (refer to SPM, 70-25-03, SP R409).
(2)
Replace a damaged or distorted cone.
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MAINTENANCE MANUAL T53-L-703
COMBUSTION CHAMRFR ASSFMRLY - MAINTFNANCE PRACTICES 1.
Disassembiv/Reassemblv Combustión Chamber Assemhly A.
B.
Disassemble Combustión Chamber Assembly (1) Straighten tabs on keywashers (4, Figure 201), and remove nuts (5) and keywashers that secure combustión chamber liner assembly (1) to combustión chamber housmg assembly (3). Remove liner assembly. (2)
Remove springs (2) from six liner assembly studs.
(3)
Remove starting íuel hose assemblies and check filfer valve. (See 73- 10-07.)
Reassemble Combustión Chamber Assembly (1)
Instan starting fuel hose assemblies and check tilter valve.
(2)
Place springs 1 -300-278-01 on six studs of combustión chamber liner assembly (1) and retain with petrolatum (72- 00-00, 53, Tab/e 203). CAUTION:
DO NOT FORCE LINER INTO HOUSING. CHECK AND REPOSITION STUDS IF REQUIRED.
(3)
Roíate all studs to face keyways inward and install liner assembly mto combustión chamber housing assembly (3) so that TOP index on housing and TOP index on liner are aligned. Make sure that stud keyways engage with tabs in housing.
(4)
Instan keywashers (4) and nuts (5) on liner assembly studs. Do not tighten nuts.
{5} To make sure proper alignment of combustión chamber liner assembly (1) with housing assembly (3), Install two alignment fixtures LTCT4174 on housing assembly. NOTE:
Protrusion of stud threads beyond nut is not required.
(6)
Tighten nuts on studs 20 to 30 inch pounds torque. Bend tabs of keywashers to secure nuts.
(7)
Remove alignment fixtures LTCT4174.
HoneyweII
1. 2,
COMBUSTION CHAMBER LINER ASSEMBLY SPRING
3. 4. 5.
COMBUSTION CHAMBER HOUSING ASSEMBLY KEYWASHER NUT
Combustión Chamber Assembly Figure 201
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MAINTENANCE MANUAL T53-L-703
COMBUSTION CHAMRFR IINFR ASSFMRIY - MAINTFNANCE PRACTICES 1.
Inspection/Check Combustión Chamber Liner Assemblv A. Inspect Líner Assembly (1)
(2)
Inspect iiner assembly for cracks in all areas. (See 72-40-03, Figure 201.) (a) (b)
Any number of 1/8 inch long cracks are allowed in liner at conical section lüuvers. Any number of cracks progressing to a louver are acceptable in each fuel nozzle area provided that each cracked louver is separated from the nejct cracked louver by an unaffected louver. (See Figure 201.)
(c)
One of four weldments may be cracked on each fuel nozzle seal guide.
Inspect inner and outer liner for cracks. (a)
Cracks between two holes are acceptable without repair except in areas shown. Ten nonadjacent cracks per assembly are allowed. (See Figure 202, Sheet 2.) CAUTION: DO NOT STOP DRILL CRACKS.
(b)
Divergent cracks originating at the base of the slots on the inner and outer iiners are acceptable up to 3/4 inch on all slots. Oniy one crack shall be allowed per slot.
(c)
A total of Uve cracks up to l inch in lengtb are acceptable on both inner and outer Iiners, provided they are nonconvergent, tight lipped, and there is no possibility of material fallout.
(d)
Cracks in up to 30 resistance welds are acceptable without repair in each liner to liner or liner to flange weidment provided no more than four adjacent tabs are affecled.
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MAINTENANCE MANUAL T53-L-703
ACCEPTABLE CRAC UJ < S
^
^ CJ T O “
ftend repair to inelude shroud end.
(c)
If distance between two damaged areas is less than twice depth of deeper damage, make One repair area. If distance between two damaged areas is greater than iwice depth of deeper damage. make sepárate repair areas. (See Figure 203.)
(d)
Damage that cannot be completely eliminated by allowabíe blade repairs are cause for rotor replacement. (See step (6).)
Repair blade surface as follows; (a)
Máximum permissible decrease in thickness at any point on blade shall be 0.010 inch.
(b)
Máximum permissible finished single repair on blade surface shall be 0.200 square inch on either concave or convex side.
(c)
Repairs shall be blended to a minimum of twice depth of damage.
(d)
Total repaired surface area shall not exceed 10 percent of blade surface.
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MAINTENANCE MANUAL T53-L-703
>*HEN THE DISTANCE BETwEEN THE D AMAGE IS CREATER THAN TWICE THE DEPTH OF THE OEEPER OAMAGE, M AKE SEP ARATE REPAIRS
WHEN THE DISTANCE BETWEEN THE O AMAGE 15 LES5 TH AN TWICE THE OEPTH OF THE OEEPER DAMAGE MAKE O NE REPAIR AREA
Power Turbine Blade Damage Before and After Repair Figure 203
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HoneyweII MA,NTENANCE^MANUAL
(5)
(e)
If distance between two damaged areas is less than twice depth of deeper damage. make one repair area. if distance between two damaged areas is greater than twice depth ot deeper damage, make sepárate repair areas. (See Figure 203.)
(f)
Damage that cannot be completely eliminated by allowable blade repairs is cause for rotor replacement-
Reseat blades recessed more than 0.025 inch below aft face of disc as follows: NOTE:
No. 1 blade is first blade counterclockwise from balancing 0-mark on forward face of disc.
(a)
Lócate and mark No. 1 blade on both sides using yellow marking pencíí (72 - 00 - 00, 47. Table 203).
(b)
Place rotor, forward face up, in fixture assembly LTCT2072. NOTE:
(c)
Make sure that blade being tapped is not positioned over slot in fixture assembly.
Starting with No. 1 blade, tap ali blades flush with aft face of disc using a hammer and a suitable dnft from punch and drift kit LTCT552. CAUTION:
MAKE SURE THAT TOOL DOES NOT CONTACT DISC OR BLADES DURING DRIVING OPERATION.
(d)
Using a hammer and a drive punch, redrive all pins.
(e)
Remove staking tool (if used),
NOTE:
If both first and second stage power turbine rotors are replaced, the new rotors shall be initially installed with yellow “H" markings (if presen!) which denote the heavy balance point 180 degrees apart.
(6)
Replace first stage turbine rotor if disc is cracked or if rubs on blade tips exceed inspection limits.
(7)
Blades damaged beyond established limits shall be replaced. Forward rotor to Overhaul for blade replacement and balancing.
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HoneyweII “A,NTENANC_E^MANUAL SECOND STAGF POWFR TURBINE Nn77l F - MAINTENANCE PRACTICES 1.
Insoection/Check Second Staae Power Turbine Nozzle A. Inspect Second Stage Power Turbine Nozzle (1) Inspect nozzle assembly for cracks, dents, nicks, burns and burrs. (a)
Any number ot 1/8 inch cracks are acceptable in trailing edge oí all vanes. (See Figure 201.)
(b)
Any number of 1/16 inch cracks on leading edge of all vanes or any number oí 1/8 inch cracks are acceptable on leading edge oí 15 vanes.
(c)
Any number of cracks are acceptable on vane to shroud brazements, including overhang. NOTE; The 10 inner shroud cracks (see step (d)) may origínate at aft edge of inner shroud and progress forward through the vane brazement or parent metal and connect with the cracks in the seal support-
(d)
A máximum of ten cracks which travel from shroud trailing edge completely around vane brazements to leading edge are acceptable provided each crack is separated by a mínimum of five vanes. These cracks are nof allowed to extend into the support sheet metal (see figure 203). Cracks up to 3/8 inch are allowed on trailing edges of inner shroud, máximum of three adjacent vanes. Máximum of 12 vanes total. {See Figure 201.) CAUTION:
ANY EVIDENCE OF TURBINE WHEEL RUBBING ON SUPPORT IS UNACCEPTABLE.
(e)
Circumferential cracks at or adjacent to Inner shroud to support joint or in support parent metal is unacceptable.
(f)
Deleted
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MAINTENANCE MANUAL T53-L-703
HoneyweII
CIRCUMFERENTIAL CRACKS NOT ACCEPTA6LE
i3je 1A2
Second Stage Power Turbine Nozzle Crack Limits Figure 201
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Sepf30 02
HoneyweII
MAINTENANCE MANUAL T53-L-703
15 AXIAL CRACKS 1/2 INCH LONG ACCEPTABLE 5 OF 15 UP TO 3/4 INCH ALLOWED
Second Stage Power Turbine Nozzle CIrcumferential Crack LImits Figure 202
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MAiNTENANCE MANUAL T53-L'-703
10 CRACKS RUNNING AXIALLY ACROSS ENTIRE INNER SHROUD SEPARATED BY FIVEVANES BETWEEN CRACKS
INNER SHROUD VANE PEQ
CRACKS IN SEAL SUPPORT NOT ALLOWED
SEAL SUPPORT (FLAT)
XA 1338 U4
Secontí Stage Power Turbine Nozzle Inner Shroud Crack Limits Figure 203
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¡lyweil
MAINTENANCE MANUAL T53-L-703
CAUTiON: ANY EVIDENCE OF TURBINE ROTOR RUBBING ON SUPPORT IS UNACCEPTABLE, REGARDLESS OF CiRCUMFERENTIAL CRACKS LENGTH. (g)
Circumferential cracks in the parent metal on inner shroud are not permitted. NOTE:
Most oí the cracking will occur in the trailing edge of vane areas of shroud.
(h)
On outer shroud trailing edge, fitteen axial cracks are allowed provided length of each crack does not exceed í/2 inch. Five of the fifteen are allowed to be cracked up to 3/4 inch and one is permitted which progresses from the shroud edge, traveis adjacent to vane and terminales at cylinder radius. (See Figures 202 and 204.)
(i)
Circumferential cracks in outer shroud are not permitted.
(j)
A máximum of four nicks or dents are allowed on vane leading edge provided that depth of any defect does not exceed 3/32 inch and length does not exceed 3/16 inch after blend repair (see Figure 205). Separation of deíects shall be at least twice the length of the shortest defect after blend repair. Smooth dents within limits are acceptable without blend repair.
(k)
A máximum of four nicks or dents are allowed on vane trailing edge provided that depth of any defect does not exceed 3/32 mch and length does not exceed 3/16 inch after blend repair. Separation of defects shall be least twice the length oí the shortest defect with blend repair. Smooth dents within limits are acceptable without blend repair.
(l)
Nicks and dents on vane airfoil surfaces are acceptable on all vanes with blend repair. Replace nozzle if limits specified in steps (j), (k) and (I) are exceeded.
(m)
Burns in leading and trailing edges of vanes are not allowed.
(n)
Cracks in seai brazement are not acceptable.
(o)
Burrs are acceptable on vane leading and trailing edges after blend repair. tnspect nozzle assembly for rubs. Axial rubs resulting from contad with turbine rotor are not permitted regardtess of circumferential crack length.
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MAINTENANCE MANUAL T53-L-703
CVLINOER RADIUS
Second Stage Power Turbine Nozzle Outer Shroud Crack Limits Figure 204
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MAINTENANCE MANUAL T53-L-703
Second Stage Power Turbine Nozzle Repair ümits Figure 205
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HoneyweII -,NT«MANUAL 2.
Cleanina/Painting Second Staae Power Turbine Nozzie Clean Second Stage Power Turbine Nozzle (72-40-00. 56, Figure 209) Using Dry Cleaning Solvent {72-00-00, 62, Table 203)
3.
Aporoved Reoairs Second Staae Power Turbine Nozzle Clean Second Stage Power Turbine Nozzle Replace if inspection limils are exceeded.
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HoneyweII POWER TURBINE ROTOR AND BEARING HODSING ASSEMBLY - MAINTENANCE PRACTICES 1.
Disassembiv/Reassemblv Power Turbine Rotor and Bearing Housina Assemblv A. Disassemble Power Turbine Rotor And Bearing Housing Assembly (1)
Place power turbine rotor and bearing housing assembly in holding tixture LTCT4553-
(2)
Straighten lock cup (17, Figure 201), Using wrench assembly LTCT915, remove nut (16). Remove lock cup.
(3)
Remove screws (18) and cover (19),
(4)
Remove impeller (20) and ring (21).
(5)
Remove screws (22) and retaining ring (23).
(6)
Install bearing housing mechanical puller LTCT4800 on bearing housing (26). Pulí bearing housing from turbine rotor (2).
(7)
Using hammer and suitable brass Orift, tap bearing (24) out of bearing housing. Remove shim (25).
(8)
Cut lockwire and remove bolts (4) and deflector support (5).
(9)
Remove seal housing (10) and impeller (12). Remove retaining ring (6) from seal housing assembly. Using arbor press or bushing and base assembly LTCT4947, press seal (8) out of seal housing. Remove packing (9) from seal housing.
(10)
Remove tube (30) and packing (29). Remove packing (31) from bearing housing.
(11)
Remove screws (14) and ring assembly (15). Remove seal (11) from bearing housing (26) and from ring assembly (15). Discard packing.
(12)
Remove bearing (28) and spacer (27) from bearing housing.
(13)
Using mechanical puller LTCT4846, remove seal ring (7) and ring (13).
(14)
Remove bolts (1) and píate (3) from turbine rotor disc.
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MAiNTENANCE MANUAL T53-L-703
Power Turbine Rotor and Bearing Housing Assembly Figure 201
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MAINTENANCE MANUAL T53-L-703
KEY TO FIGURE 201 1, 2. 3. 4. 5, 6.
BOLT TURBINE ROTOR
7. 8. 9. 10. 11
SEAL RING SEAL PACKING SEAL HOUSING SFAI
12. 13. 14. 15. 16.
IMPELLER RING SCREW RING ASSEMBLY NUT
PLATE BOLT DEFLECTOR SUPPORT RETAINING RING
17. 18. 19. 20. 21. 22. 23. 24.
LOCK CUP SCREW COVER IMPELLER RING SCREW RETAINING RING BEARING
25. SHIM 26. BEARING 27. HOUSING SPACER 28. 29. 30. 31.
BEARING PACKING TUBE PACKING
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HoneyweII B. Reassemble Power Turbine Rotor and Beanng Housing Assembly (1)
Select shim {25, Figure 201) to maintain 0.003 to 0.006 inch axial pinch on outer race of bearing (24) as íollows: (a) (b)
Using vernier depth gage, measure depth oí beanng housing (Dimensión A. Rgure 202). Using micrometer. determine axial dimensión of bearing outer race (Dimensión B. Figure 202)
.
(c)
Subtract Dimensión B from Dimensión A.
(d)
Add nominal 0.005 inch to result of preceding step (3) to determine thickness of shim.
CAUTION:
TO PREVEN! POSSIBLE AXIAL SEAL MOVEMENT, MAKE SURE THAT RETAINING RING IS SEATED PROPERLY
(2)
Instan packing (9, Figure 201) into seal housing (10). Lubrícate recess in seal housing and seal (8) with shortening compound (72-00-00, 38, Table 203). Usmg arbor press or bushing and base assembiy LTCT4947, press seal with part numbers facing up, into seal housing (10). Install retaining ring (6) into seal housing assembiy.
(3)
instan packing (31) on tube (30). Install tube in bearing housing (26). CAUTION:
(4)
MAKE SURE THAT PIN IN OUTER RACE OF ROLLER BEARING ENGAGES SLOT IN BEARING HOUSING.
Using arbor press and suitable brass bushing, press bearing outer race (28) into bearing housing (26). NOTE:
Before instaliing seal (11), seal shall be inspected for cuts, nicks, tears, cracks, distortion, pliability and wear. If damage is noted, replace seal. If seal (11) is lo be instalied, make sure groove in bearing housing (26) is olean. Coat groove with shortening compound (72-00-00, 38, Table 203) or assembiy fluid (72-00-00, 7, Table 203) to facilítate holding seal in housing.
(5)
Align screw holes in ring assembiy (15) with screw holes in bearing housing (26) and inserí ring assembiy into bearing housing. Secure ring assembiy to beanng housing with screws (14). Tighten screws (14) finger-tight (not to exceed 10 inch-pounds), then back off 1/4 to 1/2 turn. Make sure ring is not co*cked. install seal (11) in íorward groove of bearing housing (26) and on ring assembiy (15).
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HoneyweII
MAINTENANCE MANUAL T53-L-703
BEARiNG HOUSING
NO J BALL BEARINO
>iA-;38-238
Establishing Shim Thickness Figure 202
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HoneyweII ---A™ (6)
Instan packing (29) on end oí tube (30).
(7)
Place impeller (12) in ring assembly (15). Install sea! housing (10) over impeller. Make sure that tube (30) is properly seated in seal housing.
(8)
Position deflector support (5) on seal housing (10) so that cut out in deflector is aligned with boss on seal housing.
(9)
Coat threads of botts (4) with antiseize compound (72-00-00, 15, Table 203). Thread bolts into bearing housing (26) and tighten 70 to 75 inch pounds torque. Lockwire bolts. (See Figure 202A.) NOTE:
Do not lubrícate bolts.
(10)
Position píate (3, Figure 201) on turbine rotor (2) and secure píate with bolts (1). Tighten bolts 25 lo 30 inch pounds torque.
(11)
Using arbor press and suitable brass bushing, press seal ring (7) onto turbine rotor shaft.
(12)
Using arbor press and suitable brass bushing, press ring (13) onto power turbine shaft. Make sure that tangs on rings are aligned with slots in impeller (12) when performing step (13). CAUTIQN:
(13)
MAKE SURE SEAL RIDES ONTO SEAL RING WITHOUT DAMAGING THE SEAL. MAKE SURE SEAL IS LUBRICATED BEFORE INSTALÜNG THE BEARING HOUSING,
Instan power turbine rotor in suitable holding fíxture. Instad bearing housing assembly on turbine rotor. CAUTIQN:
PACK ROLLERS WITH SHORTENING COMPOUND SO THAT ROLLERS RETRACT INTO THE BEARING CAGE. MAKE SURE ROLLERS REMAIN IN CAGE WHILE BEARING !S BEING PRESSED ON TO SHAFT. INSTALL BEARING WITH PART NUMBER DOWN.
(14)
Using arbor press and sieeve bushing LTCT3493, press bearing (inner race and rollers) (28) onto power turbine shaft.
(15)
Place spacer (27) on power turbine shaft. NOTE:
(16)
Use shim having corred thickness as determinad in preceding step (1),
Instad shim (25) inte bearing housing (26).
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Honeywell
MAINTENANCE MANUAL T53-L-703
Lockwiring of Boits Figure 202A
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HoneyweII (17)
Using arbor press and sieeve bushing LTCT3493, press bearing (24) onto power turbina shatt and into bearing housing.
(18)
Instan retaining ring (23) mío bearing housing and aíign screw holes. Secure ring assembly (o bearing housing with screws (22). Tighten screws (22) finger tight (not to exceed 10 inch pounds), then back off 1/4 to 1/2 turn. Make sure ring is not co*cked.
(19)
Using arbor press and suítable brass bushing, press ring (21) onto power turbine shaft. Install impeller (20) and align slots in impeller with tangs on ring (21).
(20)
Instan cover (19). Secure cover to retaining ring (23) with screws (18). NOTE:
2-
Do not lubricate nut.
(21)
Instan power turbine rotor in holding fixture LTCT4553. Install lock cup (17) and nut (16). Usmg wrench LTCT915, tighten nut 225 lo 250 foot pounds torque.
(22)
Secure nut (16) by deforming lock cup (17) into Slot in nut at two locations.
Insoection/Check Power Turbine Rotor and Bearing Housing Assemblv A. Inspect Power Turbine Rotor and Bearing Housing Assembly NOTE: Conduct a visual inspection of the second stage power turbine rotor using a 7 power magnífyíng glass. (1)
Inspect leading and trailing edges of blade for nicks, dents, cracks ano burns. (a)
Máximum permissible finished repair depth is 0.047 inch from leading edge and 0.034 inch from trailing edge. (See Figure 203.) Allowable Oepths decrease as distance between damage and point A on leading edge or point B on trailing edge decreases. (See Figure 203.)
(b)
No dents are allowed within 0.500 inch of blade platform.
(c)
No burns or cracks are allowed.
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MAINTENANCE MANUAL T53-L-703
ALL DiMENSiONS ARE IN INCriES «A 1 ^8
Second Stage Power Turbine Blade Repair Limits Figure 203
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HoneyweII --“--A. (2)
Inspect trailing edge ol blades for erosión occurring immediately under blade shrouds. A notch visible withou; magnification is nol allowed. (See Figure 204.)
(3)
Inspect blade surfaces for nicks, denls, cracks and burns.
(4)
(a)
No dents are allowed within 0.500 inch of blade platform.
(b)
No burns or cracks are allowed.
Inspect blade tip (shroud end) for cracks and scoring. (a) (b)
Cracks in shroud are not permitted. Tip rubs shall not exceed 0.030 inch in depth. Indications of tip rub are acceptable provided tip clearance can be obtained at assembiy.
(5)
Inspect blade platform and root areas and turbine disc for cracks. No cracks are allowed.
(6)
Inspect aft side of rotor disc for blades recessed below disc. (a)
If one or more blades are recessed more than 0.025 inch, remove rotor and reseat blades.
(7)
Inspect oil passages in ring assemblies and bearing housing for cloggmg. Use deán, dry air to inspect for dogging. Ciogging is not acceptable.
(8)
Inspect impetlers for galling, scoring and loss of protective finish.
(9)
(a)
Galling or deep scoring which penetrales into parent metal Is unacceptable.
(b)
Replace if any degree of surface finish loss is evident.
inspect internal spline for wear. Wear up to 0.005 inch depth is acceptable.
3. Cleanina/Paintina Power Turbine Rotor and Bearina Housina Assemblv Clean All Parts Using Dry Cleaning Solvent (Refer to SPM, 70-15-03, SP C203)
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MAINTENANCE MANUAL T53-L-703
UOSSOF MAT ERIAL OCCURS IN THISAREA
KA
1338
M’
Second Stage Power Turbine Repair Location Figure 204 MBA A A AJI Page21l
72—50 “04 sept 30/02
HoneyweII 4.
Approved Recairs Power Turbine Rotor and Bearing Housing Assemblv A. Repair Power Turbine Rotor and Bearing Housing Assembl/ (1)
Reclean parís if oil passages are clogged.
(2)
Observe following rules dunng power turbine rotor blade repair. (a) Use portable power drill or rotary file equipped with carbide burr. lí these are not available, small diesinker type file or India or carborundum stone may be substituted.
(3)
(b)
Fmish strokes shall be parallel to leading and trailing edges of blades.
(c)
Final polísh area with crocus doth (72 - 00 - 00, 13, Tabfe 203j. Ai( repairs shail be ' blended and finished smoothly.
(d)
Blend leading or trailing edge repairs to smooth radius as part of repair. (See Figure 203.)
(e)
Finish repair length shal) be blended to mínimum of three times depth of damage.
Repair leading and/or trailing edges of power turbine rotor blades as follows: (a) (b)
Round bottom dents, 0.010 inch deep or less, require removal oí sharp edges oniy. If dístance between damage and shroud end of blade is less than twice depth of damage, extend repair to inelude shroud end.
(c)
If dístance between two damaged areas is less than twice depth of deeper damage, make one repair area. If dístance between two damaged areas is greater than twice depth of deeper damage, make sepárate repair areas. (See Figure 203.)
(d)
Damage that cannot be completely eliminated by allowable blade repair is cause for rotor replacement. Forward rotor to Overhaul for blade replacement and baiancmg.
¡4) Repair blade surfaces as follows: (a)
Máximum permissible decrease in thickness at any point on blade is 0.010 inch.
(b)
Máximum permissible finished single repair on blade surface is 0.200 square inch on either concave or convex side.
(c)
Blend repairs to mínimum oí twice depth of damage.
(d)
Total repaired surface area shall not exceed 10 percent oí blade surface.
(e)
II dístance between two damaged areas is less than twice depth of deeper damage, make one repair area. If dístance between two damaged areas ¡s greater than twice depth of deeper damage, make sepárate repair areas, (See Figure 203.)
(f)
Damage that cannot be completely eliminated by allowable blade repairs is cause for rotor replacement. Forward rotor to Overhaul tor blade replacement and balancing.
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Page 2i2 Sept 30/02
HoneyweII (5)
Reseat blades recessed more than 0.025 inch below att face of disc as follows: (a)
Lócate and mark No. 1 blade on both sides using yellow marking pencil (72-00-00, 47, Tab)e 203). NOTE:
(b)
No. 1 blade is lirst blade counterciockwise from balancing O-mark on forward face of disc.
Place rotor, forward face up, in staking fixture assembly LTCT2072. NOTE:
Make sure that blade being tapped is not positioned over Slot in fi>cture assembly.
(c)
Starting with No. 1 blade, tap all biabes fiush with att face of disc using a hammer and a suitabie drift from punch and dnft kit LTCT552.
(d)
Using staking tool assembly LTCT3738 on mushroomed pins or a hammer and a drive punch on recessed pins, redhve all pins. CAUTION:
(e)
MAKE SURE THAT TOOL DOES NOT CONTACT DISC OR BLADES DURING DRIVING OPERATION.
Remove staking tool (if used).
(6)
Replace power turbine rotor if disc is cracked or if rubs on blade tips exceed inspection limits.
(7)
Blades damaged beyond established limits shall be replaced. Forward rotor to Overhaul for blade replacement and balancing.
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Honeyuvell GAS PRODUCER SYSTFM COMPONENTS - MAINTENANCE PRACTICES J.
Disassembiy/Reassemblv Gas Producer Svsiem Componants A. Disassemble Gas Producer System Components (1) Check second stage gas producer rotor tor minimum tip clearances. Insert leeler gage betweeo second stage gas producer turbina rotor DIade tips (37, Figure 201, Sheet 2) and second stage gas producer cylinder (44) at the 12 o’clock position. CAUTION: DO NOT USE LEAD PENCIL TO MARK BLADE. (2)
Roíate lurbine rotor and check and record minimum tip clearance (longest blade). Mark longest blade with marking pencil (72-00-00, 47, Table 203).
(3)
Check clearance between tip of longest blade and fíange al seven additional positions (see Figure 202). Hold teeler gage stationary at each position and turn rotor one full turn. If tip clearance ai any position is 0.024 inch or less, rework cylinder.
(4)
Engage tangs of Socket wrench LTCT13456 (detail of LTCT13175) with nut (45, Figure 201, Sheet 2) to prevent compressor rotor shaft from turning.
(5)
Be sure to matchmark al) gas producer íurbine parts including bolts with white opaque ink (72-00-00, 73A. Table 203).
(6)
Straighten tabwashers (38) and remove nuts (39) and tabwashers that secure second stage gas producer turbine rotor (37) to spacer (33).
(7)
Using puller LTCT691, carefutly remove second stage gas producer turbine rotor (37) and spacer (33). NOTE:
(8)
Use thumbscrews to position the arms into spacer. When arms are in position, firmly lock ihem with knurled cup and back otf thumbscrews at least one half turn to allow puller to opérate freely and prevent binding of thumbscrews.
Using mechanical puller LTCT4842, remove spacer (33) and sealmg disc (36) from rotor (37).
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MAINTENANCE MANUAL T53-L-703
TTTTnrr 12
30
Gas Producer System Components Figure 201 (Sheet 1 of 2)
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TV
HoneyweII
Gas Producer System Components Figure 201 (Sheet 2)
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MAINTENANCE MANUAL T53-L-703
KEY TO FIGURE 201 1. 2. 3. 4. 5. 6. 7. 8. 9. 10. 11.
FORWARDSEAL FORWARD OlL RING SPACER RETAINING RING BEARING INNER RACE AND ROLLERS SEAL REAR BEARING HOUSING ASSEMBLY SCREW BEARING OUTER RACE COMBUSTION CHAMBER DEFLECTOR FIRST STAGE TURBINE N0Z2LE ASSEMBLY 12. BOLT 13. PACKING 14. PACKING 15. GASKET 16. RETAINING PLATE 17. GASKET 18. AFT OlL RING 18A. SEAL AND RETAINER ASSEMBLY 19. RETAINING RING 20. SEAL 21. RETAINER 22. SEALING RING 23. SHIM 24. FORWARD CONE
25. 26.
BOLT FIRST STAGE GAS PRODUCER TURBINE ROTOR ASSEMBLY 27. SPACER 28. BOLT 29. SCREW 30. PACKING 31- RING 32. SECOND STAGE TURBINE NOZZLE 33. SPACER 34. EXPANSION RING 35. SEALING RING 36. SEALING DISC 37. SECOND STAGE GAS PRODUCER TURBINE ROTOR 38. TABWASHER 39. NUT 40. BOLT 41. SEAL RING 42. RETAINING PLATE 43. PIN 44. SECOND STAGE GAS PRODUCER CYLINDER 45. NUT 46. LOCKRING 47. REAR CONE
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12:00
Checking Positions - Tip Clearance Figure 202
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HoneyweII NT~MA.UA. NOTE:
I
(9) (10)
If disassembly will inelude removing the No. 2 bearing, the engme must be removed from helicopter and positioned vertically.
Deleted. Remove two sealing rings (41) from outside diameter of second stage gas producer cylinder (44), CAUTIQN:
BOLTS (40) ARE NOT TO BE REUSED FOR REASSEMBLY.
(11)
Remove 20 bolts (40) that secure second stage gas producer cylinder to first stage turbine nozzle(ll). Remove three retaining piales (42). Discard bolts (40).
(12)
Using locating pin removal tool LTCT4692, remove pins (43). Remove second stage gas producer cylinder (44).
(13)
Remove sealing ring (35) and two expansión springs (34) from outside diameter of second stage gas producer nozzle. Remove ring (31), spacer (27), and second stage turbine nozzie (32).
(14)
Record thickness of spacer (27) for reassembiy.
(15)
Check first stage gas producer rotor for mínimum tip clearances as follows: (a)
Insert feeler gage with 1/4 inch wide tip between first stage gas producer turbine rotor (26) and first stage turbine nozzfe (11) at 12 o’ctock position. CAUTIQN:
(16)
DO NOT USE LEAD PENCIL TO MARK BLADE.
(b)
Rotate turbine rotor and check and record minimum tip clearance (tongest blade). Mark longest blade with yellow pencil (72-00-00, 47, Table 203).
(c)
Check clearance between tip of longest blade and flange at seven additional positions (see Figure 202). Hold feeler gage stationary at each position and turn rotor one full turn. If tip clearance at any position is 0.020 inch or less, first stage gas producer nozzle must be reworked or replaced.
Straighten tabs of compressor shaft rear lockring (46, Figure 201, Sheet 2). NOTE:
Make sure that bolts are drawn completely through fixture.
(17)
Instan torque fixture LTCT13175 over bolts (25) of first stage gas producer turbine rotor (26), engaging tangs of socket wrench LTCT13456 (detail of LTCT13175) with slots in nut (45). Secure fixture with nuts (39).
(18)
Using torque wrench PD2501, remove nut (45) and lockring (46).
(19)
Remove nuts (39). torque wrench and torque fixture.
(20)
Using cone removal tool LTCT6465, remove first stage gas producer turbine rotor (26) and rear cone (47).
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HoneyweII — (21)
Using white opaque ink {72-00-00, 73A, Table 203) índex botts (25) lo rotor assembly for corred reassembiy. Remove bolts Irom rotor assembly.
(22)
Remove eight bolts (28) that secure sealing ring (22). Remove seahng ring.
(23)
Remove three screws (29) that secure seal and retainer assembly (18A). Remove seal and retainer assembly (18A).
(24)
Using adapter and guide LTCT3685 and puller LTCT2121, remove aft oil ring (18), lorward cone (24) and shim (23).
(25)
Remove gasket (17), retaining píate (16), packing (30) and gasket (15). CAUTION:
IN FOLLOWING STER BOLTS (12) SHALL BE DISCAROED. INSTALLATION OF USED BOLTS DURING REASSEMBLY MAY RESULT IN BOLT FRACTURE DURING ENGINE OPERATION.
(26)
Remove eight bolts (12) that secure first stage turbine nozzle (11) and combustión chamber deflector (10) to rear bearing housing assembly (7). Discard bolts (12).
(27)
Remove first stage turbine nozzle (l 1) and combustión chamber deflector (10).
(28)
Remove two screws (8). Remove bearing housing assembly (7), packings (13, 14) and seal (6). Bearing outer race (9) will remain in bearing housing assembly (7).
(29)
Using arbor press and suitable sieeve, press bearing outer race (9) from rear bearing housing assembly (7). CAUTION:
KEEP BEARING INNER RACE AND ROLLERS AND BEARING OUTER RACE TOGETHER AS A SET.
(30)
Using mechanical puller LTCT4809, remove bearing inner race and rollers (5) from compressor rear shaft. (See Figure 203.)
(31)
Using puller LTCT4846 or LTCT4700, remove fonward oil ring (2, Figure 201, Sheet 1).
(32)
Remove retaining ring (4) and spacer (3).
(33)
Using forward seal puller LTCT4568 with arbor LTCT4571 remove forward seal (1). NOTE: With No. 2 bearing removed, fhe engine must not be moved from vertical position.
B. Reassemb/e Gas Producer System Components NOTE:
Seáis 1-300-616-01 and 1-300-173-01/-02/-03 are manufactured with three spiits in the carbón seáis, 120 degrees apar!. These spiits are not defects and are not cause for seal replacement.
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HoneyweII (1)
Reassemble components as follows: NOTE: (a)
To prevent too! rotation when using installing tool LTCT13070, engage tangs of tool with cutouts in seal (1, Figure 201, Sheet 1 ).
Carefully position lorward seal (1. Figure 201, Sheet 1) on forward oil ring 1-100-146-02/-04 (2) and using installing tool LTCT13070, install seal and ring as a unit on rear compressor shaft. Make sure top marking on seal is located at 12 o’clock position and that scalloped side oí seal is toward rear oí engine. (See Figure 204 lor proper seal instailation.) CAUTION:
(b)
TO PREVENT POSSIBLE AXIAL SEAL MOVEMENT, MAKE SURE THAT RETAINING RING IS SEATED PROPERLY.
Install spacer (3) and retaining ring (4).
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Removing Compressor Rear Bearing Figure 203
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Proper Installation of Forward Seal Figure 204
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Honeywell (c)
Using installing tool LTCT791, install bearing inner race rollers (5) on compressor rear shaft. CAUHQN: MAKE SURE OIL HOLES )N BEARING OUTER RACE UNE UP WITH OiL PASSAGE IN REAR BEARING HOUSING ASSEMBLY WITH OIL HOLES FORWARD. MAKE SURE THAT PIN IN OUTER RACE OF BEARING ENGACES SLOT IN BEARING HOUSING ASSEMBLY.
(d)
Using arbor press and suitable sleeve, press bearing outer race (9) into rear bearing housing assembíy (7) with oil boles forward.
(e)
Insta// sea/ (6) and packings (13, 14) in grooves of diffuser housing assembíy. Instan bearing housing onto air diffuser. Aliñe hole pattern. Secure with two screws (8) hand tighten screws. CAUTION:
INSTALL NEW BOLTS. INSTALLATION OF USED BOLTS MAY RESULT IN BOLT FRACTURE DURING ENGINE OPERATION,
(f)
Lubrícate eight bolts (12) with antiseize thread compound (72-00-00, 15, Table 203) ano temporarily install bolls (12) onto bearing housing. Tighten bolts (12) to 150 to 165 inch pounds and tighten screws (8) 18 to 20 inch pounds.
(g)
Lubrícate gasket (15) with shortening (72-00-00. 38, Table 203) and install In groove on bearing housing.
(h)
Lubrícate two packings (30) with shortening (72-00-00, 38, Table 203) and install in grooves on píate. Install píate, ground side down, onto bearing housing. Aliñe holes.
(i)
Lubrícate gasket (17) with shortening (72-00-00. 38, Table 203) and instad in groove on píate.
(j)
Using installer LTCT3685, install aft oil ring (18) into seal and retainer assembíy (18A). Install Seal assembíy with ring onto píate and aliñe holes. Secure sea! assembíy with three screws (29) and tighten 18 to 25 inch pounds. Instad eight bolts (28) and torque 95 to 105 inch pounds and retorque screws (29) 18 to 25 inch pounds. Then remove eight bolts (28).
(k)
Remove eight bolts (12) from bearing housing assembíy. NOTE:
Lubrícate bolts with antiseize thread compound (72-00-00, 15, Table 203).
(() Insta!! deflector assembíy (10) and nozzle assembíy (11) with eight bolls (12). Torque bolts 150 to 165 inch pounds.
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(m) (m) Lockwire (72-00-00, 40. Table 203) bolts (12).
NOTE: Bolts (28) should be lubricated with antiseize thread compound (72-00-00, 15, Table 203). (n) (n)
Instan sealing ring (22) with eight bolts (28) onto bearing housing assembly and seal assembly. Tighten bolts 85 to 95 inch pounds. Wait 5 minutes and retorque bolts (28) to 95 to 105 inch pounds. Lockwire (see Figure 205) making sure that lockwire does not interfere with air slots, and tails of lockwire are inboard of sealing ring.
(o) (o)
Select nominal shim (23) and instan onto rotor shaft. Record shim thickness.
(P) (P)
NOTE:
(q) (q)
(r) (r)
(s)
(t) (t)
(u) (u)
Use spiit cone for easy removal after clearance is established.
Use a 1-110-132-01 cone Ihat has been spiit for measuring purposes on/y to predetermine shim size. Instan wheel (26) onto rotor shaft. Check clearance “F" (see Figure 206) with LTCT14807- Press forward on rotor when checking clearance. Clearance shall be 0.095 to 0.120 in. Remove first gas producer rotor assembly. Remove spiit cone. If clearance is unacceptable. change shim (23) to proper size. Repeat steps (p) and (q) if clearance is acceptable, proceed to next step. Using installing tool LTCT4013, install forward cone (24) onto rotor shaft. Make sure cone is bottomed against aft oil ring (18). Insert six bolts (25) onto wheel (26) located by balance marks. Install wheel (26), making sure balance marks are alined. Lubrícate spiines with antiseize compound (72-00-00, 15, Table 203). Install rear cone (47) onto rotor shaft.
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XA 1333 144
Lockwire Seal Retainer Figure 205
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Determining Clearance Between First Stage Gas Producer Nozzle and Rotor Figure 206
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HoneyweII (2)
Lubrícate threads of nut (45) with antiseize compound (72-00-00, 15, Tabla 203).
(3)
Instan rea: cone (47), lockring (46) and nut (45). NOTE:
(4)
Instan torque tixture LTCT13175 over bolts (25) oí first stage gas producer turbina rotor (26), engaging tangs oí socket wrench LTCT13456 (detall oí LTCT13175) with slots m nut (45). Secura fixture with nufs (39). NOTE:
(5)
Make sure that bolts are drawn compietely through adaptar.
Nut (45) shall not extend more than 0.060 inch beyond aft tace oí cornpressor rotor rear stub shaft.
Using torque wrench PD2501, tighten nut (45) 320 to 350 loot pounds torque. Remove torque wrench and torque íixture. NOTE:
Bracket is usad as a base for dial indrcator whiíe taking runouts.
(6)
Mount bracket LTCT3955 or LTCT910 on ílange oí air difluser.
(7)
11 engine is in a maintenance stand, position engme in approximately 45 degree nose down attitude prior to perlorming steps (8) and (9). 11 engine is installed, push (orward at center oí rotor when turning lor runout measurement.
(8)
Position día) indicator against point just inboard of lirst stage gas producer turbina blade roots. Rotate gas producer turbine rotor and record runout. Runout shall be within 0.004 TIR.
(9)
Position dial indicator on rear Ilange of gas producer turbine rotor. Rotate gas producer turbine rotor and record runout. Runout sha)) be within 0.003 TIR.
(10)
Surn oí the runouts in steps (8) and (9) shall not exceed 0.006 TIR.
(11)
11 runouts are not within limits, remove lirst stage gas producer rotor, clean cones (24, 47) and reposition rotor 180 degrees from removed position. Repeat preceding step (9). II limits are still exceeded, try 90 degrees or 270 degrees from original position. 11 limits are still exceeded, replace forward cone (24) and rear cone (47).
(12)
Check first stage gas producer turbine rotor for mínimum of 0.020 inch tip clearance.
(13)
Bend lockring (46) into slots oí nut (45) in two places, 180 degrees apart. Do not shear lockring.
(14)
Remove bracket LTCT3955 or LTCT910 from air difluser. CADTIQN:
SPACER 1-120-029-01 O R- 0 3 (27) MUSI BE INSTALLED AGAINST THE SECOND STAGE TURBINE NOZZLE FLANGE AT ALL TIMES. ADDITIONAL SPACERS 1-120-029-01. -02 OR -03 MAY BE INSTALLED AS NECESSARYTO OBTAIN PROPER CLEARANCE.
(15} instan spacer (27) and ring (31) onto first gas producer nozzle. Instaíl second stage turbine nozzle (32). Align bolt holes and install pins (43). Install four equatly spaced "C” clamps to ho)d nozzle (32). Tighten clamps.
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HoneyweII -,N™NCE^MANUAL (16)
Using LTCT14807 wire gage, check axial clearance between aft face of wheel (26) and forward face of nozzle (32). Clearance shall be 0.080 to 0.105 in. If not, change spacer (27) as required. NOTE:
(17)
When installing sealing ring (35), make sure that pinching or binding does not exist in the sealing ring groove of second stage turbine nozzle.
Instan two expansión springs (34) and sealing ring (35) into groove on OD of second stage turbine nozzle. CAUTIQN:
DO NOT APPLY LUBRICANT TO UNDERSIDE OF BOLT MEAD, SINCE THIS MAY LEAD TO OVERTORQUING. EXCESSIVE TORQUE MAY CAUSE FRACTURE OF THE BOLTS.
(18)
Lubrícate threads of new bolts (40) with antiseize compound (72-00-00, 15, Table 203).
(19)
With shims, nozzle, cylinder, alignment pins and retaining piales in place, instan all bolts finger tight.
(20)
Tighten all bolts 35 to 40 inch-pounds torque, using standard torque wrench (0 to 50 inchpounds range) and a 1/4 inch universal socket or wrench extensión TMRX-8 (Snap-On Tool Corp.. Kenosha, Wisconsin or equivalent) mounted at 90 degree angle to the torque wrench centeriine. NOTE:
Resistance torque shall be a minimum of 3 inch-pounds. If lower than 3 inch-pounds replace swaged nut. (Refer to Repair Manual, 72-09-30.)
(21)
Release torque by turning bolt counterclockwise two full turns.
(22)
Using torque wrench ( 0 to 50 inch-pounds range) roíate clockwise to estabiish resistance torque of swaged nut.
(23)
Tighten bolt an additional 15 to 20 inch-pounds above this resistance torque.
(24)
Lockwire bolts. The bolt heads shall be double wired with 0.032 inch lockwire in groups of two or three.
(25)
Instan two seal rings (41) into grooves on OD of second stage gas producer cylinder. NOTE:
Spacer (33) and sealing disc (36) are a balanced pair.
(26)
Align matchmarks of spacer (33) and sealing disc (36). then using an arbor press, install spacer (33) into sealing disc.
(27)
Align matchmarks on spacer (33) and first stage gas producer rotor then position spacer (33) and sealing disc (36) on first stage gas producer turbine bolts.
(28)
Rotate gas producer rotor assembly and check for rubbing between second stage nozzle (32) and sealing disc (36). Light njb is acceptable. !f heavy rub exists, recheck runouts and inspect for distortion.
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HoneyweII ««N™™ CAUTION:
(29)
Position second stage gas producer turbina rotor (37) on spacer (33). Align all matchmarks. NOTE:
(30)
MAKE SURE FORWARD FACE OF ROTOR IS TOWARDS FRONT OF ENGINE.
Cap screws (4-40 x 3/4 inch long) may be installed in bolts (25) to facilítate alignment and installation of nut (39) while securing second stage gas producer turbine rotor (37).
Lubrícate tbreads of bolts (25) with antiseize compound (72-00-00, 15, Table 203). CAUTION:
NOTE:
WHEN INSTALLING NUTS, MAKE SURE ONLY NONMAGNETIC 0.200 INCHTHICK NUTS 1-100-293-01 ARE USED. Nuts (39) have a machined washer surface. This surface must be positioned towards the rotor assembiy.
(31)
Secure rotor with tabwashers (38) and nuts (39). Engage tangs of socket wrench LTCT13456 (detail of LTCT13175 with nut (45) to prevent compressor rotor shaft from turning. Tighten nuts evenly 170 to 180 inch pounds torque. Do not bend tabwashers at this time.
(32)
Using (LTCT14807) 0.050 inch wire gage, check clearance between aft face of inner shroud oí second stage turbine nozzle and forward face of second stage gas producer turbine rotor assembiy. Clearance must be 0.050 inch to 0.128 inch. If desired clearance is not obtamed, replace spacer (27) as required to obtain clearance. NOTE:
If engine is in maintenance stand, position engine in approximately 45 degree nose down attitude prior to per forming steps (33) and (34). If engine is installed, push forward on the center of the second gas producer rotor when turning for runout measurement.
(33)
Position dial indicator against point just inboard of second stage gas producer turbine blade roots (Figure 207, Sheet 1). Rotate gas producer turbine rotor and record runout. Runout shall be within 0.004 TIR.
(34)
Position dial indicator on step, inboard of bolt circle (Figure 207, Sheet 2). Rotate gas producer turbine rotor and record runout. Runout shail be within 0.003 TIR.
(35)
The sum of runouts in steps (33) and (34) shall not exceed 0.006 TIR.
(36)
If runouts are not within limits. loosen then retighten nuts (39, Figure 201, Sheet 2). Bend tangs of tab washers against fíats of nuts after runouts have been established.
(37)
Check second stage gas producer rotor for minimum of 0.020 inch tip clearance.
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Checking Runout on Second Stage Gas Producer Turbina Rotor Figure 207 (Sheet 1 of 2)
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MAINTENANCE MANUAL T53-L-703
Checking Runout on Second Stage Gas Producer Turbina Rotor Figure 207 (Sheet 2)
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Honeywell MA,NTENANCE^MANUAL SECOND STAGE GAS PRODUCER TURBINF ROTOR ASSEMBLY. SPACER. CYLINDER AND N077LE ASSEMBLY - MAINTENANCE PRACTtCES 1 • Inspection/Check Second Staae Gas Producer Turbine Rotor Assemblv Soacer. Cvlinder and N022le Assemblv NOTE:
A.
B.
Conduct visual inspection of second stage gas producer rotor, using a 7 power magnifying glass.
Inspect Second Stage Gas Producer Cylinder (See 72-51-00, 44, Figure 201.) (1)
Visually inspect using a 7 power magnifying glass, for cracks. If cracks are evident, replace cylinder.
(2)
Dye penetrant inspect or florescent penetrant inspection. (Refer to SPM, 70-20-04, SP 1304 or SPM, 70-20-05, SP 1305.)
(3)
Inspect ID of cylinder for nicks or dents. Blend repair. (Refer to SPM, 70-25-01, SP R401.)
(4)
Inspect cylinder for loss of dry film lubricant coating. (Refer to 290.3 Overhaul Manual.)
(5)
Inspect 12.428 to 12.430 inch diameter of cylinder (see Figure 201) for grooving. If grooving does not exceed 0.005 inch depth, cylinder is acceptabie. Replace if limits are exceeded.
(6)
Inspect 12.194 to 12.208 inch diameter al aft edge of cylinder for chipping. Chipping defects within 0.125 inch of aft edge of cylinder are acceptabie. Replace if chipping is not withm limits.
(7)
Inspect cylinder for stripped, crossed or damaged threads. Replace if damage is evident.
Inspect Second Stage Gas Producer Nozzle (1) Nozzle vanes for cracks, dents, nicks, burrs, burning and spalling. (See Figure 202.) NOTE: Do not measure cracks from any portion of manufacturer’s blend repair. When cracks occur in this area, use vane leading or trailing edge as a reference point. (See Figure 203.) (a) Any number of 1/8 inch cracks are acceptabie on trailing edge of all vanes.
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XA 1338 -Í70
Second Stage Gas Producer Cylinder Diameter Limits Figure 201
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MAINTENANCE MANUAL T53-L-7Q3
CRACKS EM ANATING FROM VANE LEADING EDGE ACCEPTABLE PHOVIOEO THEY 00 NOT EXCEED 5/16 INCH ON A MAXIMUM OP 10
CRACKS IN NOZZLE
Second Síage Gas Producer Nozzle Repair Limits Figure 202 (Sheet 1 oí 2)
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CAUSE MATERI AL ARE NOT PERMITTED
FALLCUT
tA
n33
t62
Second Stage Gas Producer Nozzle Repair Limits Figure 202 (Sheet 2)
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SeconO Stage Gas Producer Nozzle Repair Limits Figure 203
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HoneyweII -.TENANCE^ (b)
Any number of 1/16 inch cracks are acceptable on leadmg edge of all vanes. Any number of 1/8 inch cracks are acceptable on leading edge on a máximum of 15 vanes.
(c)
Nicks and burrs are acceptable on vane leading and trailing edges after blend repair. Blending shall be limifed ío removal of Sharp surface projection. NOTE:
Do not inelude manufacturer's blend repair in measurement of burned area.
(d)
Burns on leading edge 1/16 inch in length by 3/8 inch in width on máximum of 10 vanes are allowed. Burns on trailing edge 1/8 inch in length by 1/4 inch in width on máximum of 10 vanes are allowed.
(e)
Any amount of vane spallmg (loss of surface coating) on all vanes is acceptable.
(2)
(Part No. 1-120-050-03 Oniy) Inspect feit metal seal for rubs. Rubs in feit metal seal are acceptable provided penetration to base metal is not evident and some unaffected portion remains for 360 degrees as viewed axially.
(3)
Nozzle outer shroud for cracking.
(4)
(a)
Any number of axial cracks originating at vane leading edge areas and progressing to edge of shroud are acceptable. Ten of these cracks are allowed to continué radially up to forward face to flange radius. (See Figure 204.)
(b)
Any number of cracks at vane trailing edge and into shroud areas are acceptable up to 1/8 inch in iength.
(c)
Circumferential, converging, and vane to vane cracking is not allowed. Cracks in outer shroud locations, other than those noted in steps (a) and (b) are not acceptable.
Inspect tang areas for bending and mutilation. (a)
Tangs that are bent síightly {5 degrees or less) are acceptable provided they are coid straightened. After straightening, inspect area for cracks using dye penetrant method. No cracks are allowed.
(b)
Tangs that are nicked, burred or whose edges show a rolled over effect, may be blend repaired. Cracked or severely mutilated tangs are not acceptable.
(c)
Replace nozzle assembly if limits in steps (a) and (b) above are exceeded.
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Second Stage Gas Producer Nozzle Repair Limits Figure 204
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HoneyweII (5)
MAINTENANCE MANUAL T53-L-703
Inner shroud for cracking and axial rubs. (a)
Any number of cracks up to 1/8 inch at vane trailing edge and into shroud radius areas are acceptable. No cracking is allowed in other areas of mner shroud.
{b} Axial rubs are not allowed. (c) Replace nozzle if limits are exceeded. (6)
C.
Forward and aft supports for radial cracks emanating from the support to inner shroud functions. (a)
A máximum of four cracks are acceptable in both supports provided the length does not exceed 3/4 inch and a minimum of five vanes sepárate defects. Circumferential cracks are not allowed.
(b)
Individuafly inspect each support with respect to crack separation. Replace nozzle assembly if preceding limits are exceeded.
Inspect Second Stage Gas Producer Rotor (See 72-51 -00, 37, Figure 201.) NOTE:
(1)
Conduct visual mspection of second stage gas producer rotor, using a 7 power magnifying glass.
inspect blades for nicks and dents, Oniy 20 percent of the blades may have damage to the limits given. Blade replacement is required if limits are exceeded. (See Figure 205.) (a)
Critical area. (See Figure 205.) 1 Smooth dents and nicks not exceeding 0.030 inch on longest side and 0.010 inch deep are acceptable without rework. Damage In excess of these limits is cause for blade replacement. No repair allowed.
(b)
Areas A and B. (See Figure 205.) 1 Smooth dents and nicks not exceeding 0.190 inch on longest side and 0.015 inch deep are acceptable without rework.
(c)
Area C. (See Figure 205.) 1 Leading edge: Dents and mcks in an area tapering chordwise from 0.000 inch at the critical area to 0.025 Inch at the outboard extremity of area C are acceptable with repair.
•''■703
Se, •conast. '^9^ Gas ^oúuc '®SaPair 4
reas
HoneyweII
(d)
2
Trailing edge; Dents and nicks in an area tapering chordwise from 0.000 inch al the critical area to 0.050 inch at the outboard extremity of area C are acceptable with repair.
3
Sides: Dents or nicks not exceedmg 0.300 inch on the longest side and 0.015 inch deep atter repair are acceptable provided the origina! material thickness Is not reduced by more than 20 percent.
Area D. (See Figure 205.) 1
Leading edge: Dents and nicks in an area tapering chordwise form 0.025 inch at blade tip are acceptable with repair.
2
Trailing edge; Nicks and dents in an area tapering chordwise from 0.050 inch at area C to 0.100 inch at blade tip are acceptable with repair.
3
Blade lips; Dents and nicks not exceeding 0.250 inch on longest side and 0.125 inch from the top are acceptable after repair. Blade tip deformation up to 0.050 inch displacement and 0.100 inch in chordal width and/or radial length is permissible.
4
Sides; Dents and nicks not exceeding 0.300 inch on the longest side and 0.015 inch deep are acceptable after repair provided the original material thickness is not reduced by more than 20 percent. No more than four dents or nicks on either the convex or concave sides, which require blending, are allowable.
NOTE; Burning is indicated by melting or loss of metal. Evidence of burning usually denotes that other damage exists to the assembly. (2)
Inspect blades for burning, bending or distortion. None allowed.
(3)
Inspect all turbine rotor blades and disc for cracks. Cracks are not allowed.
(4)
Inspect all turbine rotor blades for tip rubs. Tip rubs shall not exceed 0.030 inch in depth. Indications of tip rub are acceptable provided tip clearance can be obtamed at assembiy.
(5)
Deleted-
(6)
Deleted.
(7)
Inspect aft face of rotor disc for rubs. Rubs 0.006 inch deep by 0.100 inch wide are aííowed provided no indications of extreme heat exists.
(8)
Inspect disc for fretting in spacer and sealing disc contact area. Fretting is acceptable up to 0.005 inch deep.
(9)
Inspect aft side of rotor disc for blades recessed below disc, If one or more blades are recessed more than 0.025 inch, remove rotor and reseat blades. If blades are damaged beyond limits, ship rotor to Overhaul facility for blade replacement and balance.
(10)
Inspect rubs on aft face of rotor disc. Rubs 0.006 inch deep by 0.100 inch witle are allowed provided no indications of extreme heat exists.
(11)
Deleted.
72-51-01
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HoneyweII MA,NTENANCE^MANUAL (12)
Inspect sealing disc for nozzle ruós. Rubs on forwarü outer diameter are not acceptable. NOTE:
(13) D.
Spacer and sealing disc are a matched pair. If one is replaced, both musí be replaced.
Replace sealing disc if cracked or distorted, or i< rubs are beyond limits.
Inspect Spacer (See 72-51-00, 33, Figure 201.) (1)
Inspect spacer for evidence of scoring. Scoring shall not exceed 0.005 inch in depth. If limits are exceeded replace. NOTE:
(2)
Spacer and sealing disc are a matched pair. If one is replaced, both must be replaced.
Inspect spacer for cracks or distortion. Cracks or distortion are not allowed.
E- Inspect Sealing Disc (See 72-51-00, 36, Figure 201.) (1)
Inspect sealing disc for cracks or distortion. Cracks or distortion are not allowed. NOTE:
(2)
2.
Material loss on labyrinth sea! will not normally be evident unless wear through of second nozzle felí metal occurs.
Inspect sealing disc for labyrinth seal rubs. Rubs are acceptable provided a mínimum of 0.050 inch and heíght remains.
Cleaning/Paintino Second Stage Gas Producer Turbina Rotor Assembiy. Spacer, Cvlinder and Nozzle Assemblv A. Olean Second Stage Gas Producer Turbine Rotor Assembiy, Spacer, Cylinder, Nozzle and Sealing Disc Olean, using dry cleaning solvent (72-00-00, 62. Table 203),
3.
Approved Repairs Second Staoe Gas Producer Turbine Rotor Assemblv. Spacer Cylinder and Nozzle Assemblv A.
Repair Second Stage Gas Producer Cylinder and Second Stage Nozzle (1)
Replace second stage gas producer cylinder or nozzle if inspection limits are exceeded. NOTE:
(2) B.
Spacer and sealing disc are balanced together. If one requires replacing, the assembiy requires balancing.
Replace sealing disc if cracked or distorted, or if rubs are beyond limits.
Repair Second Stage Gas Producer Turbine Rotor Assembiy (1)
Replace turbine rotor assembiy If blades or disc are cracked or distorted.
(2)
Replace spacer if cracked, distorted or if scoring exceeds a depth of 0.005 inch.
(3)
Repair second stage gas producer rotor assembiy bíades.
72-51-01
Page21i Sept 30/02
HoneyweII (12)
(nspect sealing disc for nozzíe ruDs. Rubs on forward outer diameter are not acceptaWe. NOTE:
(13) D.
MAINTENANCE MANUAL T53-L-703
Spacer and sealing disc are a matched pair. It one is replaced, both must be replaced.
Replace sealing disc if cracked or distorted, or i< rubs are beyond limits.
Inspect Spacer (See 72-51-00, 33, Figure 201.) (1)
Inspect spacer for evidence of scoring. Scoring shall not exceed 0.005 inch in depth. If limits are exceeded replace. NOTE:
(2)
Spacer and sealing disc are a matched pair. If one is replaced, both must be replaced.
Inspect spacer for cracks or distortion. Cracks or distortion are not allowed.
E- Inspect Sealing Disc (See 72-51-00, 36, Figure 201.) (1)
Inspect sealing disc for cracks or distortion. Cracks or distortion are not allowed. NOTE:
(2)
2.
Material loss on labyrinth seal will not normally be evident unless wear through of second nozzle felí metal occurs.
Inspect sealing disc for labyrinth seal rubs. Rubs are acceptable provided a mínimum of 0.050 inch and height remains.
Cleanino/Paintina Second Staae Gas Producer Turbine Rotor Assembiy. Spacer, Cvlinder and Nozzle Assemblv A. Clean Second Stage Gas Producer Turbine Rotor Assembiy, Spacer, Cylinder, Nozzle and Sealing Disc Clean, using dry cleaning solvent (72-00-00. 62, Table 203).
3.
Second Stage Gas Producer Turbine Rotor Aasembiv. Soacer. Cvlinder and Nozzle Assembiy A.
Repair Second Stage Gas Producer Cylinder and Second Stage Nozzle (1)
Replace second stage gas producer cylinder or nozzle if inspection limits are exceeded. NOTE:
(2) B.
Spacer and sealing disc are balanced together. If one requires replacing, the assembiy requires balancing.
Replace sealing disc if cracked or distorted. or if rubs are beyond limits.
Repair Second Stage Gas Producer Turbine Rotor Assembiy (1)
Replace turbine rotor assembiy if blades or disc are cracked or distorted.
(2)
Replace spacer if cracked, distorted or if scoring exceeds a depth of 0.005 inch.
(3)
Repair second stage gas producer rotor assembiy blades.
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MAINTENANCE MANUAL T53-L-703
riOilCyi/V©ll
(a)
(b)
Observe the lollowing rules during second stage gas producer rotor assembly blade repair: 1
Oniy small diesinker type or India or carborundum stone may be used for blend repair.
2
Finish strokes shall be parallel to leading and trailing edges of blades.
3
Final polishing of area shall be made with crocus cloth (72-00-00, 13, Table 203). Alt repairs should be blended smoothly.
4
Leading or trailing edge repairs shall be blended to smooth radius as part of repair. (See Figure 206.)
5
Finish repair of length shall be blended to mínimum of three times depth oí damage.
Repair nicks and dents on second stage gas producer rotor blades as follows; CAUTION: ONLY 20 PERCENT OF THE BL4DES MAY HAVE DAMAGE TO THE LIMITS GIVEN. iF BLADES ARE DAMAGED BEYOND LIMITS, FORWARD ROTOR TO OVERHAUL FOR BLADE REPLACEMENT AND BALANCING. 1
Critical area. (See Figure 205.) a No repair allowedb Smooth nicks and dents not exceeding 0.030 inch on the longest síde and 0.010 inch deep are acceptable without rework. Any damage in excess oí these limits is cause for blade replacement.
2
Area A and B. (See Figure 205.) a Smooth nicks or dents not exceeding 0.190 inch on the longest side and 0.015 inch deep are acceptable without repair. b Rework of nicks and dents shall be confined to smoothing and blending of damage not exceeding 0.190 inch on the longest side and 0.015 inch deep after repair.
3
Area C. (See Figure 205.) a On leading edge, nicks or dents in an area tapering chordwise from 0.000 inch at the critical area to 0.025 inch at the outboard extremity of area C may be repaired. Depth of allowable blend repairs shall be 0.000 inch at critical area, gradually increasing to 0.012 inch at midpoint and 0.025 inch at the extremity of area C, with a máximum of 0.100 inch in length (see Figure 206.) No more than two repair blends per edge area allowable in any one area.
72-51
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HoneyweII 3,
CleaninQ/Painling Accessorv Prive Gearbox Assemblv A. Clean accessory Orive Gearbox Assembly
4.
(1)
Clean using dry cleaning solvent (72-00-00, 62, Table 203).
(2)
Clean damaged pamt areas on gearbox assembly. (See paragraph 4.A.(2}.)
Aporoved Repairs Accessorv Prive Gearbox Assembly A. Repair Accessory Orive Gearbox Assembly (1)
Blend repair nicks, burrs and scratches. using small diesinker type files and India or Carborundum stones. Use crocus cloth (72-00-00, 13, Table 203} for final polishing. All repairs shall be blended and finished smoothly. Unes, scratches or Sharp edges that might cause concentration of stress are not permitted.
(2)
Refinish painted surfaces. (Refer to SPM, 70-30-18, SP P523-)
(3)
Replace studs if threaded portion cannot be repaired.
(4)
Replacement of tachometer drive seal. (See Figure 202.) NOTE:
It is not necessary to remove accessory drive gearbox from engine to replace tachometer drive seal.
(a)
Remove nuts (13) and washers (12) that secure tachometer drive flange and seal assembly (34) to accessory gearbox housing assembly (45).
(b)
Using tw/o 10-32 puller screws, withdraw tachometer drive flange and seal assembly from accessory drive gearbox and remove packing (36).
(c)
Using instaliing tool LTCT501 and an arbor press, remove seal (37) from beanng relamer (35). NOTE:
Seal (37) must be installed with solid side of seal case (side with parí number) facing tachometer flange drive housing.
(d)
Dip new seal (37) in lubricating oil (72-00-00, 41 or 42, Table 203). Using instaliing tool LTCT501, press seal into bearing relamer (35).
(e)
Position packing (36) on outside diameter of bearing retainer (35). Place flange and seal assembly over mounting stud and install gasket (10) and tachometer generator. Pasten with nuts (13) and washer (12).
72-60-01 ¿ZoZ
HoneyweII MA,NTEN™ANUAL 2. Inspection/Check Accessorv Prive Gfiarbox Assemblv A. Inspect Accessory Orive Gearbox Assembly (1)
inspect a(( parís for nicks, cracks, bufrs, wear and distortion.
(2)
Inspect threaded parís for crossed or damaged threads.
(3)
Inspect for evidence of leakage at tachometer drive, fuel control dnve and engine accessory drive seáis. Replace if detective,
(4)
Inspect starter generator drive gear spiines for wear as follows: NOTE: (a)
Petlorm the following procedure every 300 hours.
Remove oíd lubricant from spiines using dry cleaning solvent (72-00-00, 62, Table 203) . NOTE:
(b)
Whenever the starter generator drive gear is replaced, replace bearings.
Inspect gearbox (female) spiine lor excessive wear. if wear, indicated by step (c), exceeds one half the spIine wldth, replace the starter drive gear and bearings. NOTE:
Radial movement can be detected by placing the starter generator vertically on a work surface and tapping the spiine with a mallet.
(c)
Inspect lor radial freedom oí starter generator spiine. The total radial movement ol the spiine shall be a minimum of 3/16 inch. Reject the starter when the spiine is frozen or fails to move the required distance.
(d)
Relubricaíe spiines wifh Plasíilube Moly No. 3 or ML7 plus 2 (72-00-00, 45, Table 203).
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HoneyweII (3)
Position packing (2) in groove around drive gear.
(4)
Instan gearbox support (14, Figure 202) and gasket (33) onto gearbox. Instad two washers (15) and nuts (16) to hold support (14) in place.
(5)
Position packing (3) in recessed area around duct leading to oil filter.
(6)
Inserí drive shaft (1) into inlet housing and mesh with internal spiine of accessory drive gear and support shaft.
(7)
Position accessory drive gearbox on engine, making sure that drive shaft meshes with gearbox.
(8)
Carefully raise gearbox, until the spiine meshes with accessory drive gear and the gearbox mates with inlet housing.
(9)
Place washer 1-080-051 -01
(7) on shouldered bolí (8). Inserí bott and finger
(10)
Place washer 1-080-051-01
(10) on bolt (9). Inserí bolt and finger tighten.
(11)
Place washers (12) on boits (11). Inserí bolts and finger tighten.
(12) (13)
Place washers (4) on bolts (5). Inserí bolts and finger tighten. Using 1/4 inch drive extensión and ratchet, turn gearbox lachometer drive gear. Check through inlet housing to make sure that compressor rotor is turning. This indicates proper meshing of drive shaft.
(14)
Tighten bolts (8. 9) 400 to 475 inch pounds torque.
(15)
Tighten bolts (11) 250 to 325 inch pounds torque.
(16)
Tighten bolts (5) 100 to 120 inch pounds torque.
(17)
Lockwire bolts.
(18)
Remove two nuts (16) and washers (15) that were installed in step (4). NOTE: Lubrícate internal splines for fuel control drive shaft with lubricating oil (72-00-00,41 or42, Tab/e 203).
(19)
Insta!) starter generator gasket (18), and N, tachometer generator with gasket (10) 11 removed. Lubrícate splines using spiine lubricant (72-00-00, 45, Table 203).
(20)
Instan fuel control. (See 73-20-01.)
(21)
Instad power Priven rotary pump. (See 79-20-01.)
(22)
Connect inlet guide vane actualor seal drain hose assembly to adapter fitting on gearbox. Tighten connector as required.
(23)
Reconnect lubrication scavenge hose assemblies to accessory drive gearbox assembly.
72-60-01
tighten.
Page 206 Sept 30/02
HoneyweII
MA1NTENANCE MANUAL T53-L-703
KEY TO FIGURE 202 1. 2. 3. 4. 5. 6. 7. 8. 9. 10. 11. 12. 13. 14. 15. 16. 17. 18. 19. 20. 21. 22. 23. 24. 25. 26. 27. 28. 29. 30. 31. 32. 33. 34. 35.
GEARSHAFT AND BEARING ASSEMBLY ACCESSORY GEARBOX COVER ASSEMBLY GEARBOX COVER ASSEMBLY THRUST BEARING LINER ASSEMBLY THRUST BEARING SHIM THRUST BEARING LINER THRUST BEARING NUT WASHER GASKET COVER WASHER PACKING STRAINER PACKING NUT COVER GASKET BOLT SEAL AND HOUSING ASSEMBLY 0)L SEAL HOUSING PACKING PACKING SEAL SPANNER NUT LOCK CUP SEAL SPACER PACKING RETAINING PLATE THRUST BEARING SHIM TABWASHER BOLT GASKET TACHOMETER ORIVE FLANGE AND SEAL ASSEMBLY FLANGE TACHOMETER ORIVE
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. 63. 64. 65. 66. 67.
PACKING SEAL BOLT FUEL CONTROL ORIVE LINER PACKING SEAL SEAL ANO LINER ASSEMBLY OILPUMPDRIVEGEARSHAFTASSEMBLY FUEL CONTROL ORIVE GEARSHAFT ASSEMBLY ACCESSORY GEARBOX HOUSING ASSEMBLY COVER GASKET ROLLER BEARING STARTER GENERATOR ORIVE GEAR ASSEMBLY OIL AIR SEPARATOR ORIVE GEARSHAFT ASSEMBLY PACKING PINION GEARSHAFT AND BEARING ASSEMBLY BALL BEARING OUTER PINION GEARSHAFT ASSEMBLY PINION SHIM RETAINING RING BALL BEARING OUTER PINION LINER BEARING KEY WASHER PLAIN ROUND NUT PLUG PACKING BAFFLE BOLT SCREW SCREW SPACER PACKING
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HoneyweII
MAINTENANCE MANUAL T53-L-703
72-60-01
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HoneyweII
MAINTENANCE MANUAL T53-L-703
KEY TO FIGURE 201 1. 2. 3. 4. 5. ■ 6. 7. 8,
ACCESSORY ORIVE SHAFT PACKING PACKING WASHER BOLT ACCESSORY ORIVE GEARBOX WASHER SHOULOERED BOLT
9. 10. 11. 12. 13. 14. 15.
BOLT WASHER BOLT WASHER PACKING STRAINE R PACKING
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HoneyweII
MAINTENANCE MANUAL T53-L-703
t-ns-13?
Accessory Drive Gearbox Assembly Figure 201
72-60-01
Page 202 Sept 30/02
HoneyweII FACCES.qORY PRIVE GFARBQX Afi.QFMfit Y - MA/NTENANCF PRACTICES 1.
Removal/Installation Accessorv Prive Gearbox Assemblv NOTE:
A.
B.
If accessory drive gearbox is to be replaced, retain the power driven rotary (oil) pump, oil filter, screen and iransfer tube (14) and chip detector. Remove and retain support (see 14, Figure 202) and mounting nuts, bolts and washers.
Remove Accessory Drive Gearbox Assembly (1)
Disconnect lubrication scavenge hose assemblies from accessory drive gearbox assembly. (See Figure 201.)
(2)
Cap all hoses and fittings.
(3)
Disconnect and remove inlet guide vane actuator seal drain hose assembly from gearbox assembly.
(4)
Remove power driven rotary oil pump from accessory drive gearbox assembly. (See 79-20-01.)
(5)
Remove fue! control. (See 73-20-01.)
(6)
Remove starter generator and Ni tachometer generator, if installed.
(7)
Remove three bolts (5) and washers (4) that secure gearbox support to rear flange of inlet housing assembly.
(8)
Support accessory drive gearbox assembly (6) and remove shouldered bolt (8), bolt (9). two bolts (11) (one not illustrated) and washers (7, 10, 12).
(9)
Remove accessory drive gearbox assembly (6) and drive shaft (1) from inlet housing.
(10)
Remove packings (2, 3) from mounting face of gearbox.
(11)
Remove drive shaft (1), packings (13, 15) and strainer (14) from top of accessory drive gearbox.
Instan Accessory Drive Gearbox Assembly (1)
Instan packings (13, 15, Figure 201) on strainer (14).
(2)
Instal! strainer (14) in accessory drive gearbox assembly (6).
72-60-01
Page 201 Sept 30/0Í
HoneyweII ACCESSORY PRIVE GFARBOX ASSEMBLY - DESCRIPTION AND OPERATION 1. DescriPtion and Qperation The accesspry drive gearbox assembiy is mounted at the 6 o’clock posrtion on the exterior of the inlet housing. It is driven by a shaftgear mated to a driving gear on the compressor rotor. The gearbox provides the drive for the oil pump, fuel control, compressor rotor tachometer generator, and starter generator (not part of the engine). A magnetic chip detector drain plug is installed in the bottom of the gearbox.
72-60-01
Pago 1/2 Sept 30/02
HoneyweII ««-“-NUA. 3.
Aporoved Repairs. Air Diffuser Rear Comoressor Bearina Oil Seal Retainer. Aft Seal. Rear Bearing Housing Assemblv, Rolier Bearina, Fprward Oil Ring and Forward Seal A. Repair Air Diffuser, Rear Compressor Bearing Oil Seal Retainer Aft Seal, Rear Bearing Housing Assembly, Roiler Bearing, Forward Oil Ring and Forward Seal (1)
Blend repair nicks, burrs and scratches. (Refer to SPM, 70-25-01, SP R401.)
(2)
Deleted.
(3)
Deleted.
(4)
Deleted. NOTE: Seáis 1-300-616-01 and 1-300-173-01/-02/-03 are manufactured with three spiits in the carbón seáis, 120 degrees apart. These spiits are not defects and are not cause for seal replacement.
(5)
Repiace damaged aft sea! (see 72-51 -00, 20, Figure 201) as follows; (a)
Remove retaining ring (see 72-51 -00, 19, Figure 201) from seal retainer assembly (18A).
(b)
Using arbor press and installation and removal tool LTCT3825, press aft seal (see 72-51 -00, 20, Figure 201) from oü seal retainer (see 72-51-00, 21, Figure 201) or using arbor press and installation tool LTCT382S, remove aft seal (see 72-51 -00, 20, Figure 201) .
(c)
Instan new seal on base LTCT3826 (detall of LTCT3825) and secure with clamp LTCT3875 (detall of LTCT3825). Place seal with base and clamp in arbor press.
(d)
Heat oil seal retainer (see 72-51 -00, 21, Figure 201) to 300 to 380°F (140 to 193^C) for 20 to 30 minutes.
(e)
Remove retainer from oven and place onto seat. Position anvil LTCT3827 (detall of LTCT3825) onto retainer and seat firmfy with arbor press. CAUTIQN:
(f)
(6)
TO PREVEN! POSSIBLE AXIAL SEAL MOVEMENT, MAKE SURE THAT RETAINING RING IS SEATED PROPERLY
Reinstali retaining ring. (See 72-51 -00. 19, Figure 201.)
Deleted.
HoneyweII
MAINTENANCE MANUAL T53-L-703
AIR DIFFUSER. REAR nOMPRESSQR BEARING OIL REAL RETAINER. AFT SEAL. REAR RFARING HOURINfi ASSEMBLY. ROLLFR BFARING. FORWARD OIL RING AND FORWARD SEAL - MAINTENANHE PRACTICES 1. Insoection/Check Air Diffuser. Rear Comoressor Bearing Oil Seal Retainer, Aft Seal, Rear Bearina Housing Assembiv. Rotler Bearino. Forward Qil Ring and Forward Seal NOTE:
Seáis 1-300-616-01 and 1-300-173-01/-02/-03 are manufactured with ihree spiits in the carbón seáis, 120 degrees apart. These spiits are not defects, and are not cause for seal replacement.
A. Inspect all Parts
2.
(1)
Inspect all parts for nicks. burrs and scratches.
(2)
Inspect rear bearing housing assembly (see 72-51 -00, 7, Figure 201) for damaged threads.
(3)
Visually inspect all parts for cracks, distortion and excessive wear.
(4)
Inspect bearing retaining píate (see 72-51 -00, 16, Figure 201) for restricted oil passages.
(5) (6)
Inspect aft seal (see 72-51 -00, 20, Figure 201) for damage. Replace damaged aft seal. Inspect all accessible vanes for minor nicks, dents and burrs. Minor nicks. dents and burrs are acceptable for repair provided mutiiation has not occurred.
(7)
Inspect third row vanes for punctures. Minor punctures are acceptable provided engine performance has not been affected.
Cleanina/Paintino Air Diffuser. Rear Comoressor Bearina Qil Seal Retainer. Aft Seal. Rear Beanno Housing Assembly Roller Bearino. Forward Oil Riña and Forward Seal C/ean all París using Dry Cleaning Solvent (72-00 -00. 82, Table 203.)
HoneyweII
MAINTENANCE MANUAL T53-L-703
ACCEPTABLE
XA-1333 163
I
First Stage Gas Producen Nozzle (CurI) Assembly Repair Limits Figure 206
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Page 210 Sept 30/02
HoneyweII MA,NTENANCE^MANUAL
2.
(7)
Inspect nozzle curi for hot spots and contact gouges (Figure 206). Local hot spots and minor gouging caused by contact with the combustión chamber liner area acceptable.
(8)
Inspect swaged nuts on fonward side of cylmder tlange for damage. Replace damaged nuts.
(9)
Inspect cylinder for cracks. Any number of axial cracks, not exceeding 1/4 inch In length extending forward from back face of flange, are acceptable. No circumferential cracks are allowed.
(10)
Inspect deflector for cracks. Circumferential cracking is acceptable up to a total length of 7 Inches (cumulative or one crack).
(11)
Inspect nozzle curi for cracks. Axial cracks oniy are acceptable in tab area on adjacent tabs (stots). Replace nozzle if circumferential cracks are present. Missing tabs are not acceptable.
(12)
Inspect nozzle curi for missing tabs. One 3/8 inch long crack emanating from sawcut into tab is acceptable wtthout repair on two nonadjacent tabs.
(13)
Inspect nozzle curt tab area for axial and circumferential cracks. Limits are as follows: (a)
No missing tabs are allowed.
(b)
Axial cracks are acceptable in liner tab area. Circumferential cracks are not permitted.
Cleanino/Paintina First Staoe Gas Producer Nozzle Assembly A. Clean Rrst Stage Gas Producer Nozzle Assembly (See 72-51-00, 11, Figure 201) Clean first stage gas producer nozzle assembly using dry cleaning solvent (72-00-00, 62, Table 203) .
3.
Deleted
72-51-04
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HoneyweII
MAINTENANCE MANUAL T53-L-703
AXIAL CRACKS PROGRESSING TO RADIUS (5 ALLOWED)
First Stage Gas Producer Nozzle Assernbly Inner and Outer Shroud Irrsuection Limits Figure 205
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HoneyweII
MAINTENANCE MANUAL T53-L-703
BURNED ARE A NO BURN - THROUGH TO CORE ALLOWED
XA I33a )63
First Stage Gas Producer Nozzie Assembly Leading Edge - Burn Limits Figure 204
72-51
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HoneyweII
MAINTENANCE MANUAL T53-L-703
NO CORE PENETR ATION
XA 1338 162
First Stage Gas Producer Nozzíe Assembíy Leading Edge Limiís Figure 203
72-51-04
Page 206 Sept 30/02
HoneyweII “,NT„MANUAL CAUTíON: CONVERGING CRACKS WHICH CREATE THE POSSIBILITY OF MATERIAL FALLOUT ARE NOT ACCEPTABLE. IF CRACKS ARPEAR TO BE RADIATING TOWARDS ONE ANOTHER, NOZZLE SHOULD BE REJECTED. THE MINIMUM DISTANCE ALLOWED BETWEEN CONVERGING CRACKS IS 1/4 INCH. (d) Burned areas not exceeding 3/8 inch radial length by 1/4 inch axial length per vane are acceptable pn five vanes. (2)
Inspect leading edge of vanes for cracks and burns. (See Figure 203.) (a)
One 1/2 inch axial crack on the leading edge per vane is acceptable provided the core is not penetrated.
(b)
Any number or size of radial cracks are acceptable provided the core is not affected. NOTE:
(c)
Core is considerad affected when crack is breached and core is visible.
Burning is acceptable provided there is no burn through to the core. (See Figure 204.)
(3)
Inspect vanes for warpage and distortlon. Not acceptable. Replace nozzle assembiy.
(4)
Inspect vanes for nicks, dents and burrs. Acceptable without repair.
(5)
Inspect vanes for spalling (loss of coating), Any amount of spailing is acceptable on all vanes.
(6> Inspect vane inner and outer shroud and cylinder for cracks. (See Figure 205.) (a) (b)
Circumferentia) cracking is not aDowed. A máximum of five tight lipped axial cracks progressing to the outer shroud cylinder radius are acceptable provided defects are separated by a mínimum of eight vanes. Any number of small axial cracks in the radius area up to 1/8 inch length are allowed provided buckiing is not evident. NOTE:
(c)
Vane to vane and circumferential cracking is not allowed.
Vane inner shroud cracks at the vane leading edge to inner shroud junction area are acceptable up to 1/4 Inch on 20 vanes.
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HoneyweII
MAINTENANCE MANUAL T53-U-703
ONE CRAC
