AD 99-02-05

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AD Number:
99-02-05
Document Type:
AD Final Rules
Docket Number:
98-NM-241-AD
Subject Heading:
Airworthiness Directives; Lockheed Model L-1011-385-1 Series Airplanes
Subject:
Primary and Secondary Drive Shafts
Status:
Current
Citation:
Federal Register: January 15, 1999 (Volume 64, Number 10)
Citation Publish Date:
01/15/1999
Effective Date:
02/19/1999
Make:
Lockheed Martin Corporation
Model:
L-1011-385-1 | L-1011-385-1-14 | L-1011-385-1-15
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Superseded AD: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Superseded By: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 [64 FR 2556 No. 10 01/15/99]
Comments:
AIRWORTHINESS DIRECTIVES FINAL RULES: 99-02-05
CITATION:   [Federal Register: January 15, 1999 (Volume 64, Number 10)]

PAGE NUMBER:   [Page 2556]

DOCKET NUMBER:   98-NM-241-AD

AMENDMENT:   39-10994

AD NUMBER:   99-02-05

SUBJECT HEADING:   Airworthiness Directives; Lockheed Model L-1011-385-1 Series Airplanes

ACTION:   Final Rule

SUMMARY:   This amendment adopts a new airworthiness directive (AD), applicable to certain Lockheed Model L-1011-385-1 series airplanes, that requires modification of the power drive units and the lower drive sprocket assemblies of the galley lift system. This amendment is prompted by a report indicating that, due to fatigue cracking, the primary and secondary drive shafts of the galley lift failed and caused the galley lift to drop to the lower level, injuring a flight attendant. The actions specified by this AD are intended to prevent such fatigue cracking of the primary and secondary drive shafts, which could result in complete fracturing of the secondary shaft; such fracturing could allow the galley lift to drop to the bottom of the shaft, and could result in possible injury to crewmembers.

DATES:   Effective February 19, 1999. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of February 19, 1999.

ADDRESSES:   The service information referenced in this AD may be obtained from Lockheed Aeronautical Systems Support Company (LASSC), 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, One Crown Center, 1895 Phoenix Boulevard, suite 450, 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, Systems and Flight Test Branch, ACE-116A, FAA, Small Airplane Directorate, Atlanta Aircraft Certification Office, One Crown Center, 1895 Phoenix Boulevard, suite 450, Atlanta, Georgia 30349; telephone (770) 703-6063; fax (770) 703-6097.

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-1011-385-1 series airplanes was published in the Federal Register on October 27, 1998 (63 FR 57262). That action proposed to require modification of the power drive units and the lower drive sprocket assemblies of the galley lift system.

Comments
Interested persons have been afforded an opportunity to participate in the making of this amendment. Due consideration has been given to both comments received.

The commenters support the proposed rule.

Conclusion
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.

Cost Impact
There are approximately 148 airplanes of the affected design in the worldwide fleet. The FAA estimates that 77 airplanes of U.S. registry will be affected by this AD, that it will take approximately 16 work hours per airplane to accomplish the required modification, and that the average labor rate is $60 per work hour. Required parts will cost approximately $1,797 per airplane. Based on these figures, the cost impact of the AD on U.S. operators is estimated to be $212,289, or $2,757 per airplane.

The 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.

Regulatory Impact
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. 106(g), 40113, 44701.

§ 39.13 [Amended]
2. Section 39.13 is amended by adding the following new airworthiness directive:

REGULATORY TEXT:  
99-02-05 LOCKHEED: Amendment 39-10994. Docket 98-NM-241-AD.

Applicability: Model L-1011-385-1, L-1011-385-1-14, and L-1011-385-1-15 series airplanes, equipped with lower deck galleys; certificated in any category.

NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (c) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.

Compliance: Required as indicated, unless accomplished previously.

To prevent fatigue cracking of the primary and secondary drive shafts, which could result in complete fracturing of the secondary shaft, and consequent dropping of the galley lift to the bottom of the shaft and possible injury to crewmembers, accomplish the following:

(a) Within 18 months after the effective date of this AD, modify the power drive units and the lower drive sprocket assemblies of the galley lift system in accordance with Lockheed Service Bulletin 093-25-294, Revision 2, dated April 13, 1981.

NOTE 2: The Lockheed service bulletin references Lear Siegler, Inc., Service Bulletins 21192-25-08, Revision 1, dated October 19, 1979; 21192-25-09, dated August 17, 1979; and 65806-25-03, dated June 9, 1979; as additional sources of service information for modification of the power drive units and the lower drive sprocket assemblies.

(b) As of the effective date of this AD, no person shall install on any airplane a power drive unit of the galley lift system having Lockheed part number (P/N) 671980-191 (Lear Siegler P/N 21192-004) or a lower drive sprocket assembly having Lockheed P/N 671980-171 (Lear Siegler P/N 65806-313) unless it has been modified in accordance with this AD.

(c) 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.

(d) 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.

(e) The modification shall be done in accordance with Lockheed Service Bulletin 093-25-294, Revision 2, dated April 13, 1981, which contains the following list of effective pages:

Page Number
	
Revision Level
Shown on Page
	
Date
Shown on Page


1, 3
	
2
	
April 13, 1981


2, 4-13
	
Original
	
June 29, 1979

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 Support Company (LASSC), 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 FAA, Small Airplane Directorate, Atlanta Aircraft Certification Office, One Crown Center, 1895 Phoenix Boulevard, suite 450, Atlanta, Georgia; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

(f) This amendment becomes effective on February 19, 1999.

FOOTER: