AD 92-10-14
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Lockheed Martin Corporation | 382 | Airworthiness Directives; Lockheed Aeronautical Systems Company-Georgia Model 382 Series Airplanes |
| aircraft | Lockheed Martin Corporation | 382B | Airworthiness Directives; Lockheed Aeronautical Systems Company-Georgia Model 382 Series Airplanes |
| aircraft | Lockheed Martin Corporation | 382E | Airworthiness Directives; Lockheed Aeronautical Systems Company-Georgia Model 382 Series Airplanes |
| aircraft | Lockheed Martin Corporation | 382F | Airworthiness Directives; Lockheed Aeronautical Systems Company-Georgia Model 382 Series Airplanes |
| aircraft | Lockheed Martin Corporation | 382G | Airworthiness Directives; Lockheed Aeronautical Systems Company-Georgia Model 382 Series Airplanes |
Unsafe Condition
Fatigue cracking and subsequent decompression of the airplane due to cabin pressure issues.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Incorporate cabin pressure limitation into the AFM, reduce cabin pressure temporarily, inspect pressurized fuselage fairing support structure per specified work cards, repair cracks if found, and repeat inspections at intervals not exceeding 3,600 hours time-in-service.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within the next 10 hours time-in-service after July 31, 1989; within 45 days after the effective date of this AD; or prior to the accumulation of 6,300 hours time-in-service, whichever occurs later. Repeat inspections at intervals not to exceed 3,600 hours time-in-service.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Lockheed Aeronautical Systems Company-Georgia Model 382 series airplanes, serial numbers 3946 through 5305, inclusive.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
AFM Changes - Cabin Pressure
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_92-10-14.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 92-10-14 Document Type: AD Final Rules Docket Number: 91-NM-69-AD Subject Heading: Airworthiness Directives; Lockheed Aeronautical Systems Company-Georgia Model 382 Series Airplanes Subject: AFM Changes - Cabin Pressure Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 06/29/1992 Make: Lockheed Martin Corporation Model: 382 | 382B | 382E | 382F | 382G Product Type: Aircraft Product Subtype: Large Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: Updated RGL applicability to match AD applicability; CAR C-11-185 AIRWORTHINESS DIRECTIVES FINAL RULES: 92-10-14 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 91-NM-69-AD AMENDMENT: 39-8249 AD NUMBER: 92-10-14 SUBJECT HEADING: Airworthiness Directives; Lockheed Aeronautical Systems Company-Georgia Model 382 Series Airplanes ACTION: SUMMARY: DATES: Effective on June 29, 1992. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 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 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 (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. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_92-10-14.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 92-10-14 Document Type: AD Final Rules Docket Number: 91-NM-69-AD Subject Heading: Airworthiness Directives; Lockheed Aeronautical Systems Company-Georgia Model 382 Series Airplanes Subject: AFM Changes - Cabin Pressure Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 06/29/1992 Make: Lockheed Martin Corporation Model: 382 | 382B | 382E | 382F | 382G Product Type: Aircraft Product Subtype: Large Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: Updated RGL applicability to match AD applicability; CAR C-11-185 AIRWORTHINESS DIRECTIVES FINAL RULES: 92-10-14 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 91-NM-69-AD AMENDMENT: 39-8249 AD NUMBER: 92-10-14 SUBJECT HEADING: Airworthiness Directives; Lockheed Aeronautical Systems Company-Georgia Model 382 Series Airplanes ACTION: SUMMARY: DATES: Effective on June 29, 1992. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 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 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 (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. FOOTER:
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