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76-20-08: 76-20-08 LOCKHEED-CALIFORNIA COMPANY: Amendment 39-2742 as amended by Amendment 39-2916. Applies to Model L-1011-385 series airplanes, certificated in all categories.
Compliance required as indicated.
To prevent possible collapse of a main landing gear assembly due to failure of one or both of the two main landing gear upper side brace spherical bearing trunnion retaining bolts, accomplish the following:
(a) Within the next 75 hours' time in service after the effective date of this AD accomplish the following checks, inspections, repairs or replacements as necessary, in accordance with accomplishment instructions of the Lockheed-California Company Alert Service Bulletin 093- 32-A115, dated September 1, 1976, or later FAA-approved revisions.
(1) Prior to each flight, perform a visual check of each main landing gear upper side brace trunnion joint and verify that the two trunnion bearing cap retaining bolts P/Ns 76754-18-71 or 69680v18-71 or 69680-18-71 are in place and that no obvious structural deformation of the trunnion bearing caps P/Ns 1504393-109 or -110 has occurred.
(2) If one or both retaining bolts P/Ns 76754-18-71 or 69680v18-71 or 69680-18-71 are missing or if a structural deformation of the trunnion bearing caps P/Ns 1504393-109 or -110 appears to have occurred, before further flight replace both retaining bolts and inspect the side brace support fitting P/Ns 1504393-107 or -108 and the trunnion bearing caps P/Ns 1504393-109 or -110 for structural damage and replace or repair as necessary the parts found to be damaged.
(3) The checks required by this AD may be performed by a flight crew member.
(b) Equivalent checks, inspections, repairs and replacements may be used when approved by the Chief, Aircraft Engineering Division, FAA, Western Region.
(c) Compliance is required on or before March 31, 1978, unless already accomplished:
Accomplish the modification of the main landing gear upper side brace trunnion jointsin accordance with Paragraph 2, Accomplishment Instructions, of the FAA approved Lockheed-California Company Service Bulletin 093-32-115, Revision I, dated March 18, 1977 or later FAA approved revisions.
(d) Accomplishment of the modification of the upper side brace trunnion joints in accordance with paragraph (c) will remove the need for accomplishment of the requirements of paragraph (a).
Amendment 39-2742 became effective October 18, 1976.
This amendment 39-2916 becomes effective June 17, 1977.
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92-10-14: 92-10-14 LOCKHEED AERONAUTICAL SYSTEMS COMPANY-GEORGIA: Amendment 39-8249. Docket No. 91-NM-69-AD. Supersedes AD 89-15-03, Amendment 39- 6265.
Applicability: Model 382 series airplanes, serial numbers 3946 through 5305, inclusive, certificated in any category.
Compliance: Required as indicated, unless accomplished previously.
To prevent fatigue cracking and subsequent decompression of the airplane, accomplish the following:
(a) For airplanes that had accumulated 6,300 hours time-in-service prior to July 31, 1989 (the effective date of AD 89-15-03, Amendment 39-6265), within the next 10 hours time-in-service after July 31, 1989, accomplish the following:
(1) Incorporate the following statement into the Limitations Section of the FAA-approved Airplane Flight Manual (AFM). This may be accomplished by including a copy of this AD in the AFM.
"Aircraft cabin operating pressure is limited to 10 inches of mercury."
(2) Temporarily reduce cabin operating pressure in accordance with paragraph (a)(1) of this AD.
(b) For all other airplanes not subject to paragraph (a) of this AD: Within 10 hours time-in-service after the effective date of this AD, or prior to the accumulation of 6,300 hours time- in-service, whichever occurs later, accomplish the following:
(1) Incorporate the following into the Limitations Section of the FAA-approved Airplane Flight Manual (AFM). This may be accomplished by including a copy of this AD in the AFM.
"Aircraft cabin operating pressure is limited to 10 inches of mercury."
(2) Temporarily reduce cabin operating pressure in accordance with paragraph (b)(1) of this AD.
(c) For airplanes that had accumulated 6,300 hours time-in-service prior to July 31, 1989 (the effective date of AD 89-15-03, Amendment 39-6265), and have not been inspected in accordance with AD 89-15-03: Within 45 days after the effective date of this AD, perform an inspection of the following areas of the pressurized fuselage fairing support (FS) structure according to the specified Work Card procedures of Standard Maintenance Publication (SMP) 515-A/C, as specified in Lockheed Aeronautical Systems Company (LASC)-Georgia Service Bulletin 382-53-50, Revision 1, dated December 13, 1991:
FS477 to FS517 General Area
Work Card SP-126
FS477 Upper Web Flange
Work Card SP-224
FS497 Overhead Bulkhead Web and Tee-Outboard
S/N 3946 through S/N 4932
Work Card SP-224
S/N 4933 through S/N 5305
Work Card SP-126
FS497 Overhead Bulkhead Upper Attach Angle
Work Card SP-224
(d) For airplanes that have been inspected in accordance with AD 89-15-03: Within 3,000 hours time-in-service since the last inspection, perform an inspection of the following areas of the pressurized fuselage FS structure according to the specified Work Card procedures of Hercules Maintenance Program Plan SMP 515-A/C, as shown in LASC-Georgia Service Bulletin 382-53-50, Revision 1, dated December 13, 1991:
FS477 to FS517 General Area
Work Card SP-126
FS477 Upper Web Flange
Work Card SP-224
FS497 Overhead Bulkhead Web and Tee Outboard
S/N 3946 through S/N 4932
Work Card SP-224
S/N 4933 through S/N 5305
Work Card SP-126
FS497 Overhead Bulkhead Upper Attach Angle
Work Card SP-224
(e) For all other airplanes, not subject to paragraph (c) or (d) of this AD: Prior to the accumulation of 6,300 hours time-in-service, or within 45 days after the effective date of this AD, whichever occurs later, perform an inspection of the following areas of the pressurized fuselage FS structure according to the specified Work Card procedures of Hercules Maintenance Program Plan SMP 515-A/C, as shown in LASC-Georgia Service Bulletin 382-53-50, Revision 1, dated December 13, 1991:
FS477 to FS517 General Area
Work Card SP-126
FS477 Upper Web Flange
Work Card SP-224
FS497 Overhead BulkheadWeb and Tee Outboard
S/N 3946 through S/N 4932
Work Card SP-224
S/N 4933 through S/N 5305
Work Card SP-126
FS497 Overhead Bulkhead Upper Attach Angle
Work Card SP-224
(f) For all airplanes: At intervals not to exceed 3,600 hours time-in-service, repeat the inspections specified in, and in accordance with, the specified Work Card procedures of Hercules Maintenance Program Plan SMP 515-A/C, as shown in LASC-Georgia Service Bulletin 382-53-50, Revision 1, dated December 13, 1991:
FS477 to FS517 General Area
Work Card SP-126
FS477 Upper Web Flange
Work Card SP-224
FS497 Overhead Bulkhead Web and Tee Outboard
S/N 3946 through S/N 4932
Work Card SP-224
S/N 4933 through S/N 5305
Work Card SP-126
FS497 Overhead Bulkhead Upper Attach Angle
Work Card SP-224
(g) If cracks are found, prior to further flight, repair in accordance with the procedures contained in Appendix A of LASC-Georgia Service Bulletin 382-53-50, Revision 1, dated December 13, 1991; or in a manner approved by the Manager, Atlanta Aircraft Certification Office, ACE-115A, FAA, Small Airplane Directorate. After repair, continue to perform the repetitive inspections required by paragraph (f) of this AD.
(h) The limitations required by paragraphs (a) and (b) of this AD may be removed if one of the conditions specified in either paragraph (h)(1), (h)(2), (h)(3), or (h)(4) of this AD, is applicable:
(1) If no cracks were found as a result of the inspections performed in accordance with AD 89-15-03, Amendment 39-6265; or
(2) If any cracks were found as a result of the inspections performed in accordance with AD 89-15-03, Amendment 39-6265 were repaired in accordance with paragraph C. of that AD; or
(3) If no cracks are found as a result of the inspections required by paragraphs (c), (d), (e), or (f) of this AD; or
(4) If cracks are found as a result of the inspections required by paragraphs (c), (d), (e), or (f) of this AD, and they are repaired in accordance with paragraph (g) of this AD.
(i) An alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Atlanta Aircraft Certification Office (ACO), ACE-115A, FAA, Small Airplane Directorate. The request shall be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Atlanta ACO.
(j) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished.
(k) The inspections and repairs shall be done in accordance with Lockheed Aeronautical Systems Company (LASC)-Georgia Service Bulletin 382-53-50, Revision 1, dated December 13, 1991, which includes the following list of effective pages:
Page Number
Revision Level
Date
1 - 11, A7, A8
1
December 13,1991
A-1
Original
February 14, 1990
A2 - A6, A9 - A33
Original
Undated
This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Lockheed Aeronautical Systems Company-Georgia, Attn: Commercial and Customer Support, Dept. 73-05, Zone 0199, 86 South Cobb Drive, Marietta, Georgia 30063. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the FAA, Small Airplane Directorate, Atlanta Aircraft Certification Office, 1669 Phoenix Parkway, Suite 210C, Atlanta, Georgia; or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, DC.
(l) This amendment becomes effective on June 29, 1992.
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