Appendix F BOLING SERVICE BULLETIN 747-53-2307 STA 520 S -0 STA 400 8000 4380 STA 340 STA 260 STA 220 5-14 SIA 180 STA 140 00000 00 S-19 1 • ON S-23 SECTION 41
RIGHT SIDE FIGURE 2. EXTERNAL LAP JOINT CORROSION INSPECTION (CONTINUED) Dec 21/89 747-53-2307 Page 20
Appendix F BOEING SERVICE BULLETIN 747-53-2307 ENTRY DOOR NO. WING BODY FAIRINGS CARGO DOOR S-23 5-19 S-12 S-6 S-0
STA RIGHT SIDE STA SECTION 42 1000 520 STA 941 A = S -0 S -6 S-12 S-19 S-23
WING BODY
FAIRINGS
STA STA STA 520 11000 LEFT SIDE ENTRY DOOR NO. 2 SECTION 42 FIGURE 2. EXTERNAL LAP JOINT CORROSION INSPECTION (CONTINUED) Dec 21/89 747-53-2307 Page 21
AO 43-204 8/14/97 Appendix F BOEING SERVICE BULLETIN 747-53-2307 ENTRY DOOR NO. 3
- S-23
- S-19
- S-12 S-41 BL 0.00
- 5-61
- S-12 A →
- S-19
- S-23 STA STA 1000 1241 ENTRY DOOR 1480 NO. 3 OFWD APPLICABLE TO RA001. RA005-RA014.
RA102. RA103 AND RA201 ONLY.
= INDICATES AREA OF VISUAL INSPECTION ONLY O SECTION 44 FIGURE 2. EXTERNAL LAP JOINT CORROSION INSPECTION (CONTINUED) Dec 21/89 747-53-2307 Page 22
Appendix F BOEING SERVICE BULLETIN 747-53-2307
WING/BODY
FAIRINGS ENTRY DOOR NO. 4 CARGO DOOR S-23
- S-19 -S -12
- S-4 13
- S -4 A -
- S- 12
- 5-19
- S-23
ENTRY DOOR NO. 4
STA STA 1480 FAIRINGS WING/BODY 1961.1 SECTION 46 FIGURE 2. EXTERNAL LAP JOINT CORROSION INSPECTION (CONTINUED) Dec 21/89 747-53-2307 Page 23
Appendix F BOEING SERVICE BULLETIN 747-53-2307 ENTRY DOOR NO. 5 CARGO - S-23 DOOR
- S-19
- S-12
- BL 0.00 13
- 5-4
- S-12
- 5-19
- 5-23
ENTRY DOOR NO. 5 STA 2360 SECTION 46 STA 1961.1 FIGURE 2. EXTERNAL LAP JOINT CORROSION INSPECTION (CONTINUED) Dec 21/89 747-53-2307 Page 24
Appendix F BOEING SERVICE BULLETIN 747-53-2307 Perform the following applicable action(s):
a _ For lap joint areas with cracking or corrosion completely through the skin, repair per 747 Structural Repair Manual Subject 53-30-03 prior to fu, ther pressurized flight
b. For missing or distressed fasteners, replace fastener per 747 Structural Repair Manual Subject 53-30-03, Figure 9 or 10, prior to next pressurized flight.
c. lap joint areas with skin bulging or pillowing in excess
0.010 inch, repair per 747 Structural Repaiz Manual Subject 53-30-03 unless the following three conditions have been met:
Inspection per 747 Non-Destructive Iest Manual D6-7170, Part 6, Subject 51-00-00, Figure 5 indicates that material loss does not exceed 10 percent.
No evidence of skin cracks or corrosion completely through the skin is found.
3. For Section 46, tear straps have been reworked by temporary repair or terminating action per Service Bulletin 747-53A2279 in adjacent area.
NOTE: Adjacent area refers to the area bounded by the 3 stringer bays above and below the applicable lap joint and the closest tear strap forward and aft of the corroded area.
Where corrosion is within 5 inches of a frame, the next distant tear strap from and not the tear strap closest to that frame determines that boundary.
d. For lap joint areas where measured material loss does not exceed 10 percent, reinspect per this service bulletin at 500 flight-cycles specified in the procedure (Method I or II) being used.
Terminating action must be performed on corroded lap joint (fron forward circumferential splice to aft circumferential splice) within 30 months of being found.
e. For lap joint areas where material loss is greater than 10 percent, repair per 747 Structural Repair Manual Subject 53-30-03 prior to next pressurized flight.
For any lap splice which is required to be repaired per 747 Structural Repair Manual Subject 53-30-03, terminating action must be performed on the remaining unrepaired length of the skin panel (from forward circumferential splice to aft circumferential splice of repaired skin panel) within 15 months of the repair. If existing repairs are found during the initial visual inspection of this bulletin, terminating action must be accomplished on the remaining unrepaired length of the skin panel within 15 months of being found.
FIGURE 2. EXTERNAL LAP JOINT CORROSION INSPECTION (CONTINUED) Dec 21/89 747-53-2307 Page 25
Appendix F BOEING SERVICE BULLETIN 747-53-2307 PS, P7. P12.
(AND P126)
OVERHEAD PANELS STA 332 STA 394 FLIGHT
ENGINEER'S STATION 260 _ LAVATORY AREA
PILOTS'
STATION
UPPER DECK
OBSERVERS
STATION
STOWAGE STA 340 AREA STA 520/
TYPICAL FLIGHT DECK INSTALLATION
ALL AFFECTED CONFIGURATIONS SIMILAR FIGURE 3. FLIGHT DECK LAP JOINT INTERNAL ACCESS Dec 21/89 747-53-2307 Page 26
Appendix F BOEING SERVICE BULLETIN 747-53-2307
STA UP STA 300 330 FIGURE 3. FLIGHT DECK LAP JOINT INTERNAL ACCESS Dec 21/89 747-53-2307 Page 27
Appendix F BOEING SERVICE BULLETIN 747-53-2307
UP STA ORDO 300 STA 390 FIGURE 3. FLIGHT DECK LAP JOINT INTERNAL ACCESS (CONTINUED) Dec 21/89 747-53-2307 Page 28
8/14/97 AO 43-204 Appendix F BOEING SERVICE BULLETIN 747-53-2307 Remove the flight engineer's seat per 747 Maintenance Manual Subject 25-11-02 or operator's comparable procedure. Remove the observer's seat per 747 Maintenance Manual Subject 25-11-03 or operator's comparable procedure. Remove the crew seat per 747 Maintenance Manual Subject 25-11-05 or operator's compazable procedure.
Remove the pilot's seats per 747 Maintenance Manual Subject 25-11-01, or operator's comparable procedure.
Remove the pilots' overhead panel P5 and circuit breaker panels P7, P12 if installed). Reference 747 Maintenance Manual Subject 31-00-00.
Not shown - Cover pedestal, panels, racks, and all wire bundle connectors with plastic sheets to help prevent contamination or dangage of equipment.
dripshield removal.
NOTE: Prior to disconnecting any wire bundles from disconnect panels, removing any wire bundles from wire bundle clamps or disconnecting any separate ground wires, ensure that all wire bundles and separate wires are identified and suitably marked for reinstallation.
Remove and salvage the overhead sidewall linings, moldings, dripshields, and insulation in flight deck area per 747 Maintenance Manual Subject 25-14-01 or operator's comparable procedure.
Not show - loosen and deilect any installed pitot static tubing as required in modification areas per 747 Maintenance Manual Subject 34-11-00 or operator's comparable procedure.
Not shown - Loosen and deflect, or remove any oxygen tubing in modification areas. aS required per 747 Maintenance Manual Subject 35-00-00 operator's comparable procedure.
Not shown - Remove crew escape hatch per 747 Maintenance Manual Subject 53-21-01 or operator's comparable procedure.
FIGURE 3. FLIGHT DECK LAP JOINT INTERVAL ACCESS (CONTINUED) Dec 21/89 747-53-2307 Page 29
AG 43-204 8/14/97 Appendix F BOEING SERVICE BULLETIN 747-53-2307
FLIGHT COMPARTMENT
AFT PARTITION
FLIGHT COMPARTMENT DOOR E11 RACK ENCLOSURE
PARTITION
RIGHT CREW DOOR
LEFT CREW DOOR (IF INSTALLED)
FLOOR-MOUNTED
ESCAPE SLIDE (TYPICAL) FORWARD LEFT
PARTITION
TYPICAL UPPER DECK CONFIGURATION
WITH LEFT AND RIGHT CREW DOOR (OTHER UPPER DECK CONFIGURATIONS SIMILAR)
CENTER LIGHTED REVEAL
UPPER CLOSURE PANEL
LOWER CLOSURE PANEL
STOWAGE BIN
PSU PANEL
WINDOW REVEAL FIGURE 4. UPPER DECK LAP JOINT INTERNAL ACCESS Dec 21/89 747-53-2307 Page 30
Appendix F BOEING SERVICE BULLETIN 747-53-2307 Remove and salvage equipment and furnishings as required to gain access to STA 420 through STA 520 lap joints. Refer to the following maintenance manual subjects for removal procedure.
Maintenance Equipment Manual Subject Window Reveal 25-21-02 Sidewall and Ceiling Insulation 25-21-04 Ceiling Panels 25-22-03 Passenger Service Units 25-23-01 Forward Closets 25-24-00 Forward Right Partition 25-24-11 Forward Left Partition 25-24-12 Crew Rest Area 25-24-19 Passenger Seats 25-25-01 Wall Mounted Attendant Seat 25-25-04 Stairway Forward Right Partition 25-26-02 Stair Aft Right Partition 25-26-03 Stairway Forward Left Partition 25-26-06 Sidewall Stowage Units 25-28-15 Overhead Stowage Bins 25-28-23 Lavatories 25-40-03 Floor Mounted Escape Slide 25-68-02 Crew Entry Door 52-13-01 Flight Compartment Door 52-51-01 Not shown - Install all items which are removed in the preceding step per che applicable maintenance manual subject or operator's comparable procedure.
FIGURE 4. UPPER DECK LAP JOINT INTERNAL ACCESS (CONTINUED) Dec 21/89 747-53-2307 Page 31