AD 94-23-07
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Lockheed Martin Corporation | L-1011-385-1 | Airworthiness Directives; Lockheed Model L-1011-385 Series Airplanes |
| aircraft | Lockheed Martin Corporation | L-1011-385-1-14 | Airworthiness Directives; Lockheed Model L-1011-385 Series Airplanes |
| aircraft | Lockheed Martin Corporation | L-1011-385-1-15 | Airworthiness Directives; Lockheed Model L-1011-385 Series Airplanes |
| aircraft | Lockheed Martin Corporation | L-1011-385-3 | Airworthiness Directives; Lockheed Model L-1011-385 Series Airplanes |
Unsafe Condition
The AD addresses the potential for reduced controllability and survivability in the event of flight control malfunction or failure, necessitating modifications and inspections to enhance airplane survivability.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Accomplish modifications and inspections of the flight controls, doors, and horizontal stabilizers as per Lockheed Service Bulletin 093-27-301 and listed service bulletins. Operators may request alternative methods or compliance time adjustments via the Atlanta Aircraft Certification Office.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within 4 years after the effective date of this AD (December 21, 1994).
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Lockheed Model L-1011-385 series airplanes as listed in Lockheed Service Bulletin 093-27-301, including models L-1011-385-1, L-1011-385-1-14, L-1011-385-1-15, and L-1011-385-3.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Flight Controls, Doors, Horizontal Stabilizers
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_94-23-07.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 94-23-07 Document Type: AD Final Rules Docket Number: 94-NM-32-AD Subject Heading: Airworthiness Directives; Lockheed Model L-1011-385 Series Airplanes Subject: Flight Controls, Doors, Horizontal Stabilizers Status: Current Citation: Federal Register: November 21, 1994 (Volume 59, Number 223) Citation Publish Date: 11/21/1994 Effective Date: 12/21/1994 Make: Lockheed Martin Corporation Model: L-1011-385-1 | L-1011-385-1-14 | L-1011-385-1-15 | L-1011-385-3 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 [59 FR 59914 NO. 223 11/21/94] Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 94-23-07 CITATION: [Federal Register: November 21, 1994 (Volume 59, Number 223)] PAGE NUMBER: [Page 59914] DOCKET NUMBER: 94-NM-32-AD AMENDMENT: 39-9069 AD NUMBER: 94-23-07 SUBJECT HEADING: Airworthiness Directives; Lockheed Model L-1011-385 Series Airplanes ACTION: Final Rule SUMMARY: This amendment adopts a new airworthiness directive (AD), applicable to certain Lockheed Model L-1011-385 series airplanes, that requires various modifications and inspections of the flight controls, doors, and horizontal stabilizers. This amendment is prompted by a recommendation by the Systems Review Task Force (SRTF) for accomplishment of certain modifications and inspections that will enhance the controllability of these airplanes in the unlikely event of flight control malfunction or failure. The actions specified by this AD are intended to ensure airplane survivability in the event of damage to fully powered flight control systems. DATES: Effective December 21, 1994. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of December 21, 1994. ADDRESSES: The service information referenced in this AD may be obtained from Lockheed Aeronautical Systems Support Company, Field Support Department, Dept. 693, Zone 0755, 2251 Lake Park Drive, Smyrna, Georgia 30080. This information may be examined at the Federal Aviation Administration (FAA), Transport Airplane Directorate, Rules Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Small Airplane Directorate, Atlanta Aircraft Certification Office, Suite 210C, 1669 Phoenix Parkway, Atlanta, Georgia; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. FOR FURTHER INFORMATION CONTACT: Thomas Peters, Aerospace Engineer, Flight Test Branch, ACE-160A, FAA, Small Airplane Directorate, Atlanta Aircraft Certification Office, Suite 210C, 1669 Phoenix Parkway, Atlanta, Georgia 30349; telephone (404) 991-3915; fax (404) 991-3606. SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an airworthiness directive (AD) that is applicable to certain Lockheed Model L-1011-385 series airplanes was published in the Federal Register on June 9, 1994 (59 FR 29745). That action proposed to require various modifications and inspections of the flight controls, doors, and horizontal stabilizers. Interested persons have been afforded an opportunity to participate in the making of this amendment. Due consideration has been given to the comments received. One commenter supports the proposed rule. One commenter suggests that reworking and changing the part number of the cross-tie interlock bungees on the servo of the stabilizer, as described in Lockheed Service Bulletin 093-27-280, should be considered terminating action for reworking the bungee, as described in Lockheed Service Bulletin 093-27-279. The FAA recognizes that accomplishment of the actions in Lockheed Service Bulletin 093-27-280 is an acceptable means of compliance for accomplishment of the inspection and modification described in Lockheed Service Bulletin 093-27-279. The FAA finds that no change to the final rule is necessary, since this provision was included in NOTE 2 under paragraph (a) of the proposed rule. One commenter requests that the compliance time of four years, as specified in paragraph (a) of the proposal, be revised to coincide with parts availability. The commenter suggests a compliance time of four years after all required parts kits are available or five years after the effective date of the AD. The FAA does not concur. In developing an appropriate compliance time for this action, the FAA considered not only the degree of urgency associated with addressing the subject unsafe condition, but the availability of required parts and the practical aspect of installing the required modifications within a maximum interval of time allowable for all affected airplanes to continue to operate without compromising safety. The FAA is not aware of any parts availability problem at this time and, therefore, assumes that an ample number of required parts will be available for modification of the U.S. fleet within the proposed compliance period. However, under the provisions of paragraph (b) of the final rule, the FAA may approve requests for adjustments to the compliance time if data are submitted to substantiate that such an adjustment would provide an acceptable level of safety. The same commenter requests that the compliance time for accomplishment of Lockheed Service Bulletin 093-55-030 be extended. This commenter performs work in the area addressed by the service bulletin at heavy maintenance checks, which occur at intervals of 27,000 flight hours. The commenter suggests that even a five-year compliance time would be inadequate for accomplishment of this service bulletin. However, the commenter does not request a specific compliance time. The FAA does not concur with the commenter's request to extend the compliance time. The actions described in Lockheed Service Bulletin 093-55-030 should take only five work hours to complete. The FAA has determined that these actions can be accomplished during regularly scheduled maintenance visits (other than heavy maintenance checks) or inspection activities without having a significant adverse effect on airplane scheduling. However, paragraph (b) of the final rule does provide affected operators the opportunity to apply for an adjustment of the compliance time if data are presented to justify such an adjustment. After careful review of the available data, including the comments noted above, the FAA has determined that air safety and the public interest require the adoption of the rule as proposed. There are approximately 236 Model L-1011-385 series airplanes of the affected design in the worldwide fleet. The FAA estimates that 117 airplanes of U.S. registry will be affected by this AD, that it will take approximately 87 work hours per airplane to accomplish the required actions, and that the average labor rate is $55 per work hour. Required parts for certain modifications will be supplied by the manufacturer at no cost to operators. Required parts for certain other modifications will be minimal in cost. Based on these figures, the total cost impact of the AD on U.S. operators is estimated to be $559,845, or $4,785 per airplane. The total cost impact figure discussed above is based on assumptions that no operator has yet accomplished any of the requirements of this AD action, and that no operator would accomplish those actions in the future if this AD were not adopted. The number of required work hours, as indicated above, is presented as if the accomplishment of the actions required by this AD were to be conducted as "stand alone" actions. However, the 4-year compliance time specified in paragraph (a) of this AD should allow ample time for the modifications and inspections to be accomplished coincidentally with scheduled major airplane inspection and maintenance activities, thereby minimizing the costs associated with special airplane scheduling. The regulations adopted herein will not have substantial direct effects on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. Therefore, in accordance with Executive Order 12612, it is determined that this final rule does not have sufficient federalism implications to warrant the preparation of a Federalism Assessment. For the reasons discussed above, I certify that this action (1) is not a "significant regulatory action" under Executive Order 12866; (2) is not a "significant rule" under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. A final evaluation has been prepared for this action and it is contained in the Rules Docket. A copy of it may be obtained from the Rules Docket at the location provided under the caption "ADDRESSES." List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows: PART 39 - AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. App. 1354(a), 1421 and 1423; 49 U.S.C. 106(g); and 14 CFR 11.89. § 39.13 - [Amended] 2. Section 39.13 is amended by adding the following new airworthiness directive: REGULATORY TEXT: 94-23-07 LOCKHEED AERONAUTICAL SYSTEMS COMPANY: Amendment 39-9069. Docket 94-NM-32-AD. Applicability: Model L-1011-385 series airplanes; as listed in Lockheed Service Bulletin 093-27-301 ["Flight Controls - Modifications and Inspections - Collector Service Bulletin" (CSB)], dated June 9, 1992; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To ensure airplane survivability in the event of damage to fully powered flight control systems, accomplish the following: (a) Within 4 years after the effective date of this AD, accomplish modifications and inspections of the flight controls, modification of the doors, and modification of the horizontal stabilizers, in accordance with Lockheed Service Bulletin 093-27-301 ["Flight Controls - Modifications and Inspections - Collector Service Bulletin" (CSB)], dated June 9, 1992 (hereinafter referred to as the CSB). This paragraph requires accomplishment of certain Lockheed service bulletins identified in the CSB, as listed below. Modifications or inspections accomplished previously in accordance with earlier revisions of the service bulletins listed below are acceptable for compliance with this AD. Service Bulletin No. Revision Level Date of Issuance 093-27-A102 Original March 13, 1974 (Alert Service Bulletin) 093-27-178 Original April 30, 1979 093-27-200 2 September 28, 1982 093-27-279 1 February 1, 1984 093-27-289 Original December 3, 1984 093-27-292 3 March 28, 1991 093-52-061 1 November 1, 1974 093-55-030 1 March 20, 1991 NOTE 1: Paragraph (a) of this AD does not require accomplishment of any of the service bulletins listed in the CSB other than those identified above. NOTE 2: Accomplishment of the actions described in Lockheed Service Bulletin 093-27-280, dated December 16, 1983, is considered an acceptable means of compliance for accomplishment of the inspection and modification described in Lockheed Service Bulletin 093-27-279, Revision 1, dated February 1, 1984. (b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Atlanta Aircraft Certification Office (ACO), FAA, Small Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Atlanta ACO. NOTE 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Atlanta ACO. (c) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. (d) The modifications and inspections shall be done in accordance with Lockheed Service Bulletin 093-27-301 ["Flight Controls - Modifications and Inspections - Collector Service Bulletin" (CSB)], dated June 9, 1992. 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 Western Export Company (LWEC), Field Support Department, Dept. 693, Zone 0755, 2251 Lake Park Drive, Smyrna, Georgia 30080. 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, Suite 210C, 1669 Phoenix Parkway, Atlanta, Georgia; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on December 21, 1994. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_94-23-07.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 94-23-07 Document Type: AD Final Rules Docket Number: 94-NM-32-AD Subject Heading: Airworthiness Directives; Lockheed Model L-1011-385 Series Airplanes Subject: Flight Controls, Doors, Horizontal Stabilizers Status: Current Citation: Federal Register: November 21, 1994 (Volume 59, Number 223) Citation Publish Date: 11/21/1994 Effective Date: 12/21/1994 Make: Lockheed Martin Corporation Model: L-1011-385-1 | L-1011-385-1-14 | L-1011-385-1-15 | L-1011-385-3 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 [59 FR 59914 NO. 223 11/21/94] Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 94-23-07 CITATION: [Federal Register: November 21, 1994 (Volume 59, Number 223)] PAGE NUMBER: [Page 59914] DOCKET NUMBER: 94-NM-32-AD AMENDMENT: 39-9069 AD NUMBER: 94-23-07 SUBJECT HEADING: Airworthiness Directives; Lockheed Model L-1011-385 Series Airplanes ACTION: Final Rule SUMMARY: This amendment adopts a new airworthiness directive (AD), applicable to certain Lockheed Model L-1011-385 series airplanes, that requires various modifications and inspections of the flight controls, doors, and horizontal stabilizers. This amendment is prompted by a recommendation by the Systems Review Task Force (SRTF) for accomplishment of certain modifications and inspections that will enhance the controllability of these airplanes in the unlikely event of flight control malfunction or failure. The actions specified by this AD are intended to ensure airplane survivability in the event of damage to fully powered flight control systems. DATES: Effective December 21, 1994. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of December 21, 1994. ADDRESSES: The service information referenced in this AD may be obtained from Lockheed Aeronautical Systems Support Company, Field Support Department, Dept. 693, Zone 0755, 2251 Lake Park Drive, Smyrna, Georgia 30080. This information may be examined at the Federal Aviation Administration (FAA), Transport Airplane Directorate, Rules Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Small Airplane Directorate, Atlanta Aircraft Certification Office, Suite 210C, 1669 Phoenix Parkway, Atlanta, Georgia; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. FOR FURTHER INFORMATION CONTACT: Thomas Peters, Aerospace Engineer, Flight Test Branch, ACE-160A, FAA, Small Airplane Directorate, Atlanta Aircraft Certification Office, Suite 210C, 1669 Phoenix Parkway, Atlanta, Georgia 30349; telephone (404) 991-3915; fax (404) 991-3606. SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an airworthiness directive (AD) that is applicable to certain Lockheed Model L-1011-385 series airplanes was published in the Federal Register on June 9, 1994 (59 FR 29745). That action proposed to require various modifications and inspections of the flight controls, doors, and horizontal stabilizers. Interested persons have been afforded an opportunity to participate in the making of this amendment. Due consideration has been given to the comments received. One commenter supports the proposed rule. One commenter suggests that reworking and changing the part number of the cross-tie interlock bungees on the servo of the stabilizer, as described in Lockheed Service Bulletin 093-27-280, should be considered terminating action for reworking the bungee, as described in Lockheed Service Bulletin 093-27-279. The FAA recognizes that accomplishment of the actions in Lockheed Service Bulletin 093-27-280 is an acceptable means of compliance for accomplishment of the inspection and modification described in Lockheed Service Bulletin 093-27-279. The FAA finds that no change to the final rule is necessary, since this provision was included in NOTE 2 under paragraph (a) of the proposed rule. One commenter requests that the compliance time of four years, as specified in paragraph (a) of the proposal, be revised to coincide with parts availability. The commenter suggests a compliance time of four years after all required parts kits are available or five years after the effective date of the AD. The FAA does not concur. In developing an appropriate compliance time for this action, the FAA considered not only the degree of urgency associated with addressing the subject unsafe condition, but the availability of required parts and the practical aspect of installing the required modifications within a maximum interval of time allowable for all affected airplanes to continue to operate without compromising safety. The FAA is not aware of any parts availability problem at this time and, therefore, assumes that an ample number of required parts will be available for modification of the U.S. fleet within the proposed compliance period. However, under the provisions of paragraph (b) of the final rule, the FAA may approve requests for adjustments to the compliance time if data are submitted to substantiate that such an adjustment would provide an acceptable level of safety. The same commenter requests that the compliance time for accomplishment of Lockheed Service Bulletin 093-55-030 be extended. This commenter performs work in the area addressed by the service bulletin at heavy maintenance checks, which occur at intervals of 27,000 flight hours. The commenter suggests that even a five-year compliance time would be inadequate for accomplishment of this service bulletin. However, the commenter does not request a specific compliance time. The FAA does not concur with the commenter's request to extend the compliance time. The actions described in Lockheed Service Bulletin 093-55-030 should take only five work hours to complete. The FAA has determined that these actions can be accomplished during regularly scheduled maintenance visits (other than heavy maintenance checks) or inspection activities without having a significant adverse effect on airplane scheduling. However, paragraph (b) of the final rule does provide affected operators the opportunity to apply for an adjustment of the compliance time if data are presented to justify such an adjustment. After careful review of the available data, including the comments noted above, the FAA has determined that air safety and the public interest require the adoption of the rule as proposed. There are approximately 236 Model L-1011-385 series airplanes of the affected design in the worldwide fleet. The FAA estimates that 117 airplanes of U.S. registry will be affected by this AD, that it will take approximately 87 work hours per airplane to accomplish the required actions, and that the average labor rate is $55 per work hour. Required parts for certain modifications will be supplied by the manufacturer at no cost to operators. Required parts for certain other modifications will be minimal in cost. Based on these figures, the total cost impact of the AD on U.S. operators is estimated to be $559,845, or $4,785 per airplane. The total cost impact figure discussed above is based on assumptions that no operator has yet accomplished any of the requirements of this AD action, and that no operator would accomplish those actions in the future if this AD were not adopted. The number of required work hours, as indicated above, is presented as if the accomplishment of the actions required by this AD were to be conducted as "stand alone" actions. However, the 4-year compliance time specified in paragraph (a) of this AD should allow ample time for the modifications and inspections to be accomplished coincidentally with scheduled major airplane inspection and maintenance activities, thereby minimizing the costs associated with special airplane scheduling. The regulations adopted herein will not have substantial direct effects on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. Therefore, in accordance with Executive Order 12612, it is determined that this final rule does not have sufficient federalism implications to warrant the preparation of a Federalism Assessment. For the reasons discussed above, I certify that this action (1) is not a "significant regulatory action" under Executive Order 12866; (2) is not a "significant rule" under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. A final evaluation has been prepared for this action and it is contained in the Rules Docket. A copy of it may be obtained from the Rules Docket at the location provided under the caption "ADDRESSES." List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows: PART 39 - AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. App. 1354(a), 1421 and 1423; 49 U.S.C. 106(g); and 14 CFR 11.89. § 39.13 - [Amended] 2. Section 39.13 is amended by adding the following new airworthiness directive: REGULATORY TEXT: 94-23-07 LOCKHEED AERONAUTICAL SYSTEMS COMPANY: Amendment 39-9069. Docket 94-NM-32-AD. Applicability: Model L-1011-385 series airplanes; as listed in Lockheed Service Bulletin 093-27-301 ["Flight Controls - Modifications and Inspections - Collector Service Bulletin" (CSB)], dated June 9, 1992; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To ensure airplane survivability in the event of damage to fully powered flight control systems, accomplish the following: (a) Within 4 years after the effective date of this AD, accomplish modifications and inspections of the flight controls, modification of the doors, and modification of the horizontal stabilizers, in accordance with Lockheed Service Bulletin 093-27-301 ["Flight Controls - Modifications and Inspections - Collector Service Bulletin" (CSB)], dated June 9, 1992 (hereinafter referred to as the CSB). This paragraph requires accomplishment of certain Lockheed service bulletins identified in the CSB, as listed below. Modifications or inspections accomplished previously in accordance with earlier revisions of the service bulletins listed below are acceptable for compliance with this AD. Service Bulletin No. Revision Level Date of Issuance 093-27-A102 Original March 13, 1974 (Alert Service Bulletin) 093-27-178 Original April 30, 1979 093-27-200 2 September 28, 1982 093-27-279 1 February 1, 1984 093-27-289 Original December 3, 1984 093-27-292 3 March 28, 1991 093-52-061 1 November 1, 1974 093-55-030 1 March 20, 1991 NOTE 1: Paragraph (a) of this AD does not require accomplishment of any of the service bulletins listed in the CSB other than those identified above. NOTE 2: Accomplishment of the actions described in Lockheed Service Bulletin 093-27-280, dated December 16, 1983, is considered an acceptable means of compliance for accomplishment of the inspection and modification described in Lockheed Service Bulletin 093-27-279, Revision 1, dated February 1, 1984. (b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Atlanta Aircraft Certification Office (ACO), FAA, Small Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Atlanta ACO. NOTE 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Atlanta ACO. (c) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. (d) The modifications and inspections shall be done in accordance with Lockheed Service Bulletin 093-27-301 ["Flight Controls - Modifications and Inspections - Collector Service Bulletin" (CSB)], dated June 9, 1992. 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 Western Export Company (LWEC), Field Support Department, Dept. 693, Zone 0755, 2251 Lake Park Drive, Smyrna, Georgia 30080. 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, Suite 210C, 1669 Phoenix Parkway, Atlanta, Georgia; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on December 21, 1994. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
This site is not affiliated with or endorsed by the FAA. Always verify with official sources.
Related Airworthiness Directives
2023-10-02
final ruleAirworthiness Directives; Transport and Commuter Category Airplanes
Unsafe Condition: Radio altimeter anomalies that are undetected by the automation or pilot, particularly close to the ground (e.g., landing flare), could lead to loss of continued safe flight and landing. Additional...
2015-11-02 Recurring
final ruleAirworthiness Directives; Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Airplanes
Unsafe Condition: Simultaneous failure of multiple stringer end fittings through fatigue cracking at the aft pressure bulkhead, which could lead to rapid decompression of the airplane.
2014-20-08 Recurring
final ruleAirworthiness Directives; Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Airplanes
Unsafe Condition: Cracked rib cap castellations, which could degrade the structural capabilities of the airplane.
2013-15-18 Recurring
final ruleAirworthiness Directives; Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Airplanes
Unsafe Condition: Reports of small cracks in additional areas outside those addressed in AD 2005-15-01, prior to the inspection threshold required by AD 2005-15-01. Corrosion or fatigue cracking of certain structura...