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B757-200PCF/PCC
SERVICE BULLETIN PC-757-53A0005
ALERT Summary Page 1 of 1 PRECISION CONVERSIONS LLC, 9800 SW NIMBUS AVENUE, BEAVERTON, OREGON, 97008
Number: PC-757-53A0005 SUMMARY Date: Ma y 7, 2024 Revision: 2 ATA System: 53-00
SUBJECT: FUSELAGE - STA 333 - STRUCTURAL INSPECTION/REINFORCEMENT OF THE
LAVATORY SERVICE PANEL
BACKGROUND
Precision Conversions has received reports of cracking in the structure in and around the lavatory service panel. These were found during normal maintenance checks. The cracks occur in the lavatory service panel access pan, the stringer common to the lavatory service panel, and can extend into the fuselage skin.
An undetected crack in the skin, stringer, or access pan could result in depressurization of the airplane and/or loss of the ability to carry aircraft loads.
Revision 2 of this Service Bulletin aligns instructions with FAA requirements.
ACTION
- Complete internal and external inspections of the lavatory service panel.
- Reinforce the surround structure.
- Replace access pan if necessary.
Contact Precision Customer Support if cracks/damage beyond the limits specified in this SB are discovered.
COMPLIANCE
Precision considers compliance with this Service Bulletin to be mandatory. Refer to Paragraph I.A for compliance requirements.
EFFECTIVITY
The following 757-200 airplanes converted to Freighter by STC ST01529SE or Combi by STC ST02278SE:
Precision Line Numbers:
001-006, 007, 009-015, 017-020, 022-039, 041-077, 079-081, 083-086, 089, 092, 098, 101, 103, 106, 107, 111, 112, 114, 118, 120, 122, 124, 126, 128, 130, 131, 134-136, 139, 141, 142, 144, 145, 147, 150, 151, 153, 154, 156, 158, 159, P161, P164, P169, P170.
MANPOWER
Total labor hours – 56. See Section I.F for detailed estimate breakdown.
MATERIAL INFORMATION
Refer to Paragraph II.A., Parts Necessary for Each Aircraft.
B757-200PCF/PCC
SERVICE BULLETIN PC-757-53A0005
ALERT Revision 2 PC-757-53A0005 May 7/24 Page 1 of 38 PRECISION CONVERSIONS LLC, 9800 SW NIMBUS AVENUE, BEAVERTON, OREGON, 97008
Number: PC-757-53A0005 Date: Ma y 7, 2024 Revision: 2 ATA System: 53-00
SUBJECT: FUSELAGE - STA 333 - STRUCTURAL INSPECTION/REINFORCEMENT OF THE
LAVATORY SERVICE PANEL
THIS SERVICE BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH I.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OPERATOR.
I. PLANNING INFORMATION
A. Effectivity
Model 757-200 series airplanes converted to freighter by STC ST01529SE or combi by STC ST02278SE. The list below shows airplanes that have been converted via one of the STCs.
Registration numbers are for reference only:
Precision Line No. Model No. Line No. Variable No. Manufacturing Serial No. Registration No.
001 757-204 440 NB421 26962 VT-BDO 002 757-23A 257 NB139 24567 C-FLAJ 003 757-23A 255 NB138 24566 C-FKAJ 004 757-26DER 231 NE001 24471 HP-2110DAE 005 757-26DER 235 NE002 24472 N312AL 006 757-208ER 273 ND201 24739 TF-FIH 007 757-260ER 348 NE201 25014 N755CS 008 757-256R 553 ND241 26239 EC-FTR 009 757-28A 127 NA441 23767 C-GIAJ 010 757-225 74 NA022 22211 N314ST 011 757-225 75 NA023 22611 N511KW 012 757-225 42 NA021 22210 N241AL 013 757-225 117 NA026 22689 N689GX 014 757-225 115 NA025 22688 N688GX 015 757-23N 692 NC059 27598 VT-BDM 017 757-236 183 NA395 24121 EC-KLD 018 757-28A 130 NA442 23822 N822PB 019 757-236 279 NA343 24792 C-FKCJ 020 757-25CER 475 ND221 25898 VT-BDN 022 757-236 441 NA348 25597 VQ-BPY 023 757-21B 232 NB066 24401 B-2899 024 757-27AER 910 NT885 29611 HP-1810DAE 025 757-27AER 832 NT881 29607 HP-1910DAE 026 757-27AER 904 NT884 29610 HP-2010DAE 027 757-2Z0 554 NB293 25887 B-2832 028 757-2Z0 615 NB297 27269 B-2839 029 757-236 449 NA350 25620 OE-LNB 030 757-25CER 565 ND222 25899 B-2828 031 757-21B 389 NB262 25258 B-2817 032 757-222ER 361 NE041 25042 N531UA 033 757-25CER 574 ND223 25900 B-2829 034 757-2B6 106 NC042 23687 N557CM 035 757-2Q8 597 NC071 26273 N751CX 036 757-2Z0 674 NB302 27512 B-2845 037 757-2Z0 622 NB298 27270 B-2840 038 757-28A 704 NB224 26276 VT-BDQ 039 757-2Z0 833 NT202 29793 B-2856
B757-200PCF/PCC
SERVICE BULLETIN PC-757-53A0005
ALERT Revision 2 PC-757-53A0005 May 7/24 Page 2 of 38 PRECISION CONVERSIONS LLC, 9800 SW NIMBUS AVENUE, BEAVERTON, OREGON, 97008 Precision Line No. Model No. Line No. Variable No. Manufacturing Serial No. Registration No.
041 757-2Z0 624 NB299 27367 B-2841 042 757-2Z0 595 NB294 27258 B-2836 043 757-2Z0 822 NT201 29792 B-2855 044 757-25F 752 NB230 28718 VT-BDA 045 757-2Z0 669 NB301 27511 B-2844 046 757-29JER 588 NE301 27203 N757QM 047 757-2Z0 480 NB292 25886 B-2821 048 757-2Q8 836 NT378 29380 D-ALEN 049 757-230ER 446 NE172 25441 N888LT 050 757-2Q8 821 NT377 29443 D-ALEO 051 757-2Q8 1006 NT346 30046 D-ALEP 052 757-25F 928 NT237 30757 B-6150 053 757-222ER 421 NE147 25397 OO-TFC 054 757-2G5 671 NB446 26278 B-7342 055 757-25F 932 NT238 30758 B-7082 056 757-23N 737 NC062 27974 VT-BDB 057 757-2Q8 688 NC073 26332 D-ALEQ 058 757-23N 843 NT283 29330 D-ALEU 059 757-28A 738 NB226 27621 B-7689 060 757-2Q8 819 NT376 29442 D-ALES 061 757-2Q8 639 NC072 27351 D-ALER 062 757-23N 814 NT282 27976 OE-LNE 063 757-256ER 943 NT915 29312 OE-LNJ 064 757-236 873 NT408 29945 OE-LNF 065 757-23N 779 NT281 27975 OE-LND 066 757-25CER 685 ND224 27513 B-2848 067 757-222ER 414 NE145 25368 VP-BHM 068 757-256ER 948 NT916 30052 OE-LNU 069 757-236 445 NA349 25598 B-2835 070 757-236 877 NT409 29946 OE-LNH 071 757-2Y0 503 NB328 26156 B-2827 072 757-28A 672 NB222 26275 OE-LNC 073 757-25CER 698 ND225 27517 B-2849 074 757-21B 583 NB266 25889 B-2824 075 757-21K 746 NB571 28674 B-1432 076 757-21B 575 NB265 25888 B-2823 077 757-28A 974 NT248 32449 OE-LNI 079 757-2Y0 482 NB325 26153 B-2831 080 757-28A 865 NT239 28174 D-ALET 081 757-28A 723 NB225 28161 D-ALEV 083 757-204 528 NB428 25623 B-1578 084 757-21B 585 NB267 25890 B-2825 085 757-2Z0 613 NB296 27260 B-1463 086 757-28S 966 NT385 32342 B-2813 089 757-28S 868 NT383 29217 B-2859 092 757-28S 961 NT384 32341 B-2812 098 757-28S 1015 NT386 32343 B-2830 101 757-2B7 655 NB517 27805 B-1145 103 757-28S 811 NT382 29216 B-2853 106 757-2B7 605 NB512 27201 B-1173 107 757-28S 797 NT381 29215 B-2851 111 757-2B7 607 NB513 27244 B-208Q 112 757-230ER 382 NE166 25140 N688SL 114 757-236 864 NT404 29941 B-20AW 118 757-236 872 NT407 29944 B-20CX 120 757-236 867 NT405 29942 B-20E9 122 757-236 871 NT406 29943 B-20EF 124 757-28A 1041 NJ004 33101 B-220A 126 757-28A 1029 NJ003 33100 B-220C 128 757-28A 1026 NJ001 33098 B-220J
B757-200PCF/PCC
SERVICE BULLETIN PC-757-53A0005
ALERT Revision 2 PC-757-53A0005 May 7/24 Page 3 of 38 PRECISION CONVERSIONS LLC, 9800 SW NIMBUS AVENUE, BEAVERTON, OREGON, 97008 Precision Line No. Model No. Line No. Variable No. Manufacturing Serial No. Registration No.
130 757-256ER 940 NT914 29311 N818NH 131 757-25C 1048 NJ032 34009 B-2866 132 757-25C 1047 NJ031 34008 B-2862 134 757-256ER 616 ND246 26244 N1902S 135 757-28A 1028 NJ002 33099 B-220Z 136 757-256ER 617 ND247 26245 N286GB 139 757-25CER 1009 NN052 32942 B-2869 141 757-204 861 NT432 28836 C-GAJU 142 757-25CER 993 NN051 32941 B-2868 144 757-23N 930 NT286 30548 B-221U 145 757-256ER 897 NT905 26251 N260AS 147 757-28A 950 NT245 32446 B-222E 150 757-2G5 919 NT426 29379 C-GCJS 151 757-23N 945 NT288 30886 N204UW 153 757-2G5 922 NT427 30394 N394BR 154 757-28A 951 NT246 32447 N228DP 156 757-223ER 852 NT739 29591 N181AN 158 757-28A 967 NT247 32448 B-223M 159 757-23N 946 NT289 30887 B-223P 161 757-28A 782 NT231 28833 N28833 164 757-2G5 834 NT412 29489 N489BR 169 757-231 896 NT359 30339 UK75704 170 757-204 850 NT431 28834 VP-BOO
B. Reason Precision Conversions has received reports of cracking in the structure in and around the lavatory service panel. These were found during normal maintenance checks. The cracks occur in the lavatory service panel access pan (PN 007D4782), the stringer (S-22R) common to the lavatory service panel, and can extend into the fuselage skin.
An undetected crack in the skin, stringer, or access pan could result in depressurization of the airplane and/or loss of the ability to carry aircraft loads.
C. Description This Service Bulletin supplies instructions to perform internal and external inspections of the lavatory service panel and surround structure. If cracks are found, the service bulletin directs replacement of the access pan, if required, and repair of the surrounding structure.
D. Compliance Precision considers compliance with this Service Bulletin to be mandatory.
For this SB, some locations are marked RC START and RC END to identify instructions that are required to comply with the SB. After release of an FAA AD, an Alternative Method of Compliance (AMOC) is required for any deviations to steps between RC START and RC END, including substeps and identified figures.
Accomplish the required actions, based on the applicable conditions in Table 1, in accordance with Paragraph III – Accomplishment Instructions.
When more than one OPTION is given for a CONDITION, do only one OPTION. When more than one ACTION is given for a CONDITION or an OPTION, do all of the ACTION numbers for that CONDITION or OPTION.
B757-200PCF/PCC
SERVICE BULLETIN PC-757-53A0005
ALERT Revision 2 PC-757-53A0005 May 7/24 Page 4 of 38 PRECISION CONVERSIONS LLC, 9800 SW NIMBUS AVENUE, BEAVERTON, OREGON, 97008 Table 1: Compliance Requirements Condition Action Compliance Time (Whichever Occurs Later) Repeat Interval (Not to Exceed) ALL
AIRPLANES
1. Perform inspection of the lavatory service panel, access pan fastener holes, S- 22R stringer, and external skin per Paragraph III, Part 1, Inspection. [2] Within 5,500 flight cycles after the STC ST01529SE or ST02278SE installation.
Within 3 months after the original issue date of this Service Bulletin.
CONDITION 1:
ANY CRACK FOUND
1. Repair or replace all cracked parts per Paragraph III, Part 2, Repair.
Before further flight.
2. Install reinforcement per Paragraph III, Part 3, Reinforcement. [1] Before further flight.
CONDITION 2:
NO CRACK FOUND OPTION 1: Perform inspections of the lavatory service panel, access pan fastener holes, S-22R stringer, and external skin per Paragraph III, Part 1, Inspection.
2,000 flight cycles after initial inspection performed 2,000 flight cycles OPTION 2: Install reinforcement per Paragraph III, Part 3, Reinforcement. [1] Before further flight.
CONDITION 3:
Reinforcement installed per Paragraph III, Part 3, Reinforcement
1. Perform a Detailed Visual Inspection of the access pan corners per Paragraph III Part 1, Inspection.
Within 8,000 flight cycles after the Reinforcement Installation.
8,000 flight cycles
2. Perform an internal LFEC inspection of the external skin around all fastener holes common to acess pan per Paragraph III Part 1, Inspection.
Within 35,000 flight cycles after the Reinforcement is installed 3,500 flight cycles
3. Perform an inspection of the doubler-toskin fastener holes and skin trim area per OPTION 1:
Internal HFEC Within 40,000 flight cycles after the Reinforcement is installed 20,000 flight cycles
B757-200PCF/PCC
SERVICE BULLETIN PC-757-53A0005
ALERT Revision 2 PC-757-53A0005 May 7/24 Page 5 of 38 PRECISION CONVERSIONS LLC, 9800 SW NIMBUS AVENUE, BEAVERTON, OREGON, 97008 Condition Action Compliance Time (Whichever Occurs Later) Repeat Interval (Not to Exceed) Paragraph III Part 1, Inspection.
OPTION 2:
External LFEC Within 40,000 flight cycles after the Reinforcement is installed 13,000 flight cycles
4. Perform inspection of the lavatory service panel cover plate fastener holes per Paragraph III, Part 1, Inspection.
OPTION 1:
Internal HFEC Within 20,000 flight cycles after the reinforcement installation.
20,000 flight cycles OPTION 2:
External LFEC Within 18,000 flight cycles after the reinforcement installation.
18,000 flight cycles CONDITION 4:
Any crack is found during any postreinforcement installation inspections Contact Precision Engineering for a repair.
Before further flight.
[1] The following Engineering Authorizations issued by Precision Conversions provide repairs that constitute compliance as Condition 3 and Paragraph III, Part 3. Inspections are required after Part 3, Reinforcement as specified in Table 1.
a. Precision Conversion Number 008, MSN 26239, Precision EA 23-1051 Rev IR
b. Precision Conversion Number 056, MSN 27974, Precision EA 23-1102 Rev IR
c. Precision Conversion Number 017, MSN 24121, Precision EA 23-1153 Rev IR
d. Precision Conversion Number 161, MSN 28833, Precision EA 24-1015 Rev IR
[2] The following Engineering Authorization issued by Precision Conversions provides a repair that constitutes compliance with Part 1, Inspections. Inspections per Part 1, Existing Configuration are no longer possible. Within 2,000 flight cycles of EA incorporation, perform alternative inspections or Reinforcement Installation per Part 3. Contact Precision Conversions for alternative inspection instructions.
a. Precision Conversion Number 001, MSN 26962, Precision EA 22-1147 Rev IR
E. Approval This Service Bulletin is FAA approved.
B757-200PCF/PCC
SERVICE BULLETIN PC-757-53A0005
ALERT Revision 2 PC-757-53A0005 May 7/24 Page 6 of 38 PRECISION CONVERSIONS LLC, 9800 SW NIMBUS AVENUE, BEAVERTON, OREGON, 97008 F. Manpower The data below shows an estimate of the labor hours necessary to inspect and, if necessary, repair and/or rework the lavatory service panel installation. Adjust the estimate with operator labor hour data if necessary. The estimate does not include lost time. These are some examples of lost time:
— Time to schedule the work — Time to examine the work — Time to find the tools Task Number of Persons Labor Hours Elapsed Time (Hours) Gain Access 1 2 2 Perform Inspection 2 4 2 Reinforcement Installation 2 38 21 Close-up 1 2 23 TOTAL FOR EACH AIRPLANE (Inspection & Reinforcement) 46 23 Replace Service Pan (if necessary) 2 10 28 TOTAL FOR EACH AIRPLANE (If Service Pan Needs Replacement) 56 28
G. Material – Price and Availability See Paragraph II.A., Parts Necessary for Each Airplane H. Weight and Balance No effect I. Electrical Load Data No effect J. References
1. Data supplied with this Service Bulletin:
Document Revision Title 007D4780 F Panel Installation – Lavatory Service
NOTE: Drawing 007D4780 is for reference only. In case of contradictory information, this SB prevails.
2. Data not supplied with this Service Bulletin:
N/A
3. Drawings used to prepare this Service Bulletin:
Document Revision Title 007D4796 T Lavatory Systems Installation
B757-200PCF/PCC
SERVICE BULLETIN PC-757-53A0005
ALERT Revision 2 PC-757-53A0005 May 7/24 Page 7 of 38 PRECISION CONVERSIONS LLC, 9800 SW NIMBUS AVENUE, BEAVERTON, OREGON, 97008
a) Other Documents:
Boeing 757 SRM.
Boeing 757 AMM.
PC-0118-06 Supplemental Maintenance Manual for B757-200PCF Cargo Conversion.
PC-0118-206 Supplemental Maintenance Manual for B757-200PCC Combi Conversion.
K. Publications Affected None L. Special Tooling Necessary to Complete This Service Bulletin None. Standard maintenance shop tools can be used to implement this modification.
M. Interchangeability and Intermixability of Parts Not applicable
B757-200PCF/PCC
SERVICE BULLETIN PC-757-53A0005
ALERT Revision 2 PC-757-53A0005 May 7/24 Page 8 of 38 PRECISION CONVERSIONS LLC, 9800 SW NIMBUS AVENUE, BEAVERTON, OREGON, 97008 II. MATERIAL INFORMATION A. Material - Price and Availability Parts/Materials:
Part Number Name Quantity Notes 007D4782-3 Pan, Access 1 (b) 007D4783-11 Doubler, Access 1 (b) 007D4783-15 Plate, Access Fitting Attach 1 (b) 007F3615-1 Stringer, Lav 1 (b) HL19PB6 Hi-Lok A/R (a)(b) HL63PB6 Hi-Lok A/R (a)(b) HL19PB5 Hi-Lok A/R (a)(b) HL18PB5 Hi-Lok A/R (a)(b) HL18PB6 Hi-Lok A/R (a)(b) NAS1097KE5 Rivet A/R (a)(b) NAS1097KE5 Rivet A/R (a)(b) MS20470AD5 Rivet A/R (a)(b) Ref. SRM 51-40-08 Repair washers A/R (a)(b)
0.063” 2024-T3 AMS-QQ-A-250/5 Aluminum Clad sheet A/R (a)(c)(d)
0.080” 7075-T6 AMS-QQ-A-250/13 Aluminum Clad sheet A/R (a)(c)
(a) Parts supplied by the operator.
(b) Only if cracks are found.
(c) Stock required for local fabrication of parts
(d) Size as shown in figure 8A or 9A
B. Special Tools and Equipment
1. No special tools or equipment are necessary to do the change in this service bulletin.
B757-200PCF/PCC
SERVICE BULLETIN PC-757-53A0005
ALERT Revision 2 PC-757-53A0005 May 7/24 Page 9 of 38 PRECISION CONVERSIONS LLC, 9800 SW NIMBUS AVENUE, BEAVERTON, OREGON, 97008
III. ACCOMPLISHMENT INSTRUCTIONS Part 1 – INSPECTION A. General Information
1. If compliance with this SB is mandated by an Airworthiness Directive (AD), all applicable required actions specified must be done. For this SB, some locations are marked RC START and RC END to identify instructions that are required to comply with the AD. An Alternative Method of Compliance (AMOC) is required for any deviations to steps between RC START and RC End, including sub-steps and identified figures.
2. The compliance times for the actions in Work Instructions are in I – Planning Information, D - Compliance.
3. A Detailed Visual Inspection is defined in 757 MPD, Chapter 2 (DET).
4. If it is necessary to remove more parts for ac cess, it is permissible to remove those parts.
Follow applicable SRM, AMM, and MPD requirements.
5. If existing skin repairs are present in the area from STA 310.5 - 365.25, Stringer 20R – 24R, contact Precision Customer Support with details before beginning work.
6. Unless otherwise specified, perform inspections for any cracks, flaws, or defects per applicable MPD requirements.
CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED
MATERIAL, METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE SPARKES OR OTHER ELECTRICAL DAMAGE.
B. Work Instructions
1. Gain Access per III. Part 4 – ACCESS.
RC START
2. Inspection, Existing Configuration ALL AIRPLANES – ACTION 1 or CONDITION 2, OPTION 1
a. Perform an inspection of the la vatory service panel as follows:
i. Perform an external High-Frequency Eddy Current (HFEC) at the fastener holes common to the external skin as shown in FIGURE 11A and 11B, circle note 1.
ii. Perform the HFEC inspection per B757 NDT manual part 6, 51-00-01.
b. Perform an inspection of the access pan as follows:
i. Perform an external High-Frequency Eddy Current (HFEC) at the access pan corners as shown in FIGURE 10, circle note 1.
ii. Perform the HFEC inspection per B757 NDT manual part 6, 51-00-01.
B757-200PCF/PCC
SERVICE BULLETIN PC-757-53A0005
ALERT Revision 2 PC-757-53A0005 May 7/24 Page 10 of 38 PRECISION CONVERSIONS LLC, 9800 SW NIMBUS AVENUE, BEAVERTON, OREGON, 97008
c. Perform an inspection of the lavatory se rvice panel at fastener holes common to the cover plate as follows:
i. Perform an Internal HFEC installation of the lavatory service panel fastener holes common to the cover plate as shown in FIGURE 12, circle note 1.
ii. Perform HFEC inspection per B757 NDT manual part 6, 51-00-01.
d. Perform an inspection of the S-22R Stringer between STA 324 and 345:
i. Perform a Detailed Visual Inspection of stringer S-22R within 10 inches from the access pan direction as shown in Figure 11A, circle note 2. Refer to FIGURE 6A for typical cracking.
e. Perform a General Visual Inspection of the Lavatory Service Panel Installation and attaching structure between STA 324 to 345 and S-21R to S-23R.
3. Inspection, Reinforced Configuration CONDITION 3 — ACTION 1
a. Perform an internal and external Detaile d Visual Inspection of the access pan corners as shown in FIGURE 10, circle note 1.
CONDITION 3 — ACTION 2
b. Perform an internal low-frequency eddy curr ent (LFEC) inspection of the external skin at all fastener holes common to the access pan as shown in FIGURE 15, circle note 1.
CONDITION 3 — ACTION 3, OPTION 1
c. Perform an internal HFEC inspection of t he external skin at the outer row of fasteners common to the repair doubler as shown in FIGURE 13, circle note 1.
d. If skin trim was performed per Part 2 FIGU RE 7, perform internal HFEC inspection of the external skin around cutout at all fasteners not covered by access pan common to the repair doubler as shown in FIGURE 14, circle note 1.
CONDITION 3 — ACTION 3, OPTION 2
e. Perform an external LFEC inspection of the external skin at the outer row of the fasteners common to the repair doubler as shown in FIGURE 13, circle note 1.
f. If skin trim was performed per Part 2 FIGU RE 7, perform an external LFEC inspection of the external skin around cutout at all fasteners not covered by access pan common to the repair doubler as shown in FIGURE 14, circle note 1.
CONDITION 3 — ACTION 4, OPTION 1
g. Perform an internal HFEC inspection of t he lavatory service panel at all fastener holes common to the cover plate as shown in FIGURE 12, circle note 1.
CONDITION 3 — ACTION 4, OPTION 2
h. Perform an external LFEC inspection of t he lavatory service panel at all fastener holes common to the cover plate as shown in FIGURE 12, circle note 1.
RC END
B757-200PCF/PCC
SERVICE BULLETIN PC-757-53A0005
ALERT Revision 2 PC-757-53A0005 May 7/24 Page 11 of 38 PRECISION CONVERSIONS LLC, 9800 SW NIMBUS AVENUE, BEAVERTON, OREGON, 97008
PART 2 – REPAIR A. General Information
Note:
1. Final shape and size of rework to be determ ined on the aircraft based on fastener pattern.
2. Unless otherwise specified, apply chemical conversion coating to all repair parts and bare surfaces per SRM Chapter 51-20-01.
3. Ensure no preload on any structure due to repair installation. Maximum pull-up gap to be
0.010 inch before fastener installation. Fabricate shim if/as required per Document 010-0001.
4. Install fasteners per SRM Chapter 51-40 requi rements. Unless otherwise specified, maintain minimum 2D edge margin and 4D-6D spacing.
5. If the length of any fastener specified in this service bulletin does not meet installation standards given in 757 SRM Chapter 51, then a fastener of the same specification, or an approved substitute, with a length which meets the installation standards given in SRM Chapter 51 may be used.
6. Fay surface seal all repair parts with BMS 5-95 sealant per SRM 51-20-05.
7. Maintain min .030” clearance between edges of parts when applicable.
8. Plug any remaining fastener holes with sa me diameter type and fastener as OEM detail.
9. Use care to prevent dam age to adjacent structure.
10. All rework is to be performed IAW the appropriate AMM or SRM.
11. Wet install Hi-Loks with sealant using MIL-PRF-81733, Type IV, Class 1, Grade A.
12. Maintain 2D edge margins and 4D-6D spacing on new/existing fasteners unless specified differently.
13. Where the work instructions include installation of a kept part, a new or serviceable part with the same part number can be installed as an alternative to the kept part.
CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED
MATERIAL, METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE SPARKES OR OTHER ELECTRICAL DAMAGE.