Airworthiness directives: Lockheed,

[Federal Register: November 22, 1999 (Volume 64, Number 224)]

[Proposed Rules]

[Page 63755-63757]

From the Federal Register Online via GPO Access [wais.access.gpo.gov]

[DOCID:fr22no99-40]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-314-AD]

RIN 2120-AA64

Airworthiness Directives; Lockheed Model L-1011-385 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

SUMMARY: This document proposes the adoption of a new airworthiness directive (AD) that is applicable to all Lockheed Model L-1011-385 series airplanes. This proposal would require modifications of the engine turbine cooling air panel at the flight engineer/second officer's console, pilot's caution and warning light panel on the main instrument panel, and monitoring system for the engine turbine air temperature. This proposal is prompted by reports of an undetected fire breaching the high speed gearbox (HSGB) case on certain Rolls Royce engines installed on in-service airplanes due to lack of an internal fire detection system within the HSGB. The actions specified by the proposed AD are intended to prevent undetected fires originating within the HSGB from breaching the HSGB case, which could result in engine damage and increased difficulty in extinguishing a fire.

DATES: Comments must be received by January 6, 2000.

ADDRESSES: Submit comments in triplicate to the Federal Aviation Administration (FAA), Transport Airplane Directorate, ANM-114, Attention: Rules Docket No. 98-NM-314-AD, 1601 Lind Avenue, SW., Renton, Washington 98055-4056. Comments may be inspected at this location between 9 a.m. and 3 p.m., Monday through Friday, except Federal holidays.

The service information referenced in the proposed rule may be obtained from Lockheed Martin Aircraft & Logistics

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Center, 120 Orion Street, Greenville, South Carolina 29605. This information may be examined at the FAA, Transport Airplane Directorate, 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.

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:

Comments Invited

Interested persons are invited to participate in the making of the proposed rule by submitting such written data, views, or arguments as they may desire. Communications shall identify the Rules Docket number and be submitted in triplicate to the address specified above. All communications received on or before the closing date for comments, specified above, will be considered before taking action on the proposed rule. The proposals contained in this notice may be changed in light of the comments received.

Comments are specifically invited on the overall regulatory, economic, environmental, and energy aspects of the proposed rule. All comments submitted will be available, both before and after the closing date for comments, in the Rules Docket for examination by interested persons. A report summarizing each FAA-public contact concerned with the substance of this proposal will be filedin the Rules Docket.

Commenters wishing the FAA to acknowledge receipt of their comments submitted in response to this notice must submit a self-addressed, stamped postcard on which the following statement is made: ``Comments to Docket Number 98-NM-314-AD.'' The postcard will be date stamped and returned to the commenter.

Availability of NPRMs

Any person may obtain a copy of this NPRM by submitting a request to the FAA, Transport Airplane Directorate, ANM-114, Attention: Rules Docket No. 98-NM-314-AD, 1601 Lind Avenue, SW., Renton, Washington 98055-4056.

Discussion

The FAA has received reports of an undetected fire breaching the high speed gear box (HSGB) case on Rolls Royce Model RB211-22B and -524 series engines installed on all Lockheed Model L-1011-385 series airplanes due to lack of an internal fire detection system within the HSGB. Investigation has revealed that an internal failure (i.e., principally bearing failure) in the engine HSGB induces combustion of the lubricating oil in the gearbox. This fire can eventually burn through the gearbox housing, which is the first point where it becomes detectable with the current fire detection system. After shutting down the engine subsequent to a fire warning, the windmilling engine core will still supply sufficient air to the HSGB to sustain combustion. Undetected HSGB fires due to lack of an internal fire detection system within the HSGB, could result in engine damage and increased difficulty in extinguishing a fire.

Other Relevant Rulemaking

On June 26, 1997, the FAA issued AD 97-14-07, amendment 39-10065 (62 FR 35951, July 3, 1997), applicable to certain Lockheed Model L- 1011 series airplanes equipped with Rolls Royce RB211-524 engines, to require various modifications and corrective actions to prevent a potential fire hazard from an undetected gearbox fire.

On April 21, 1998, the FAA issued AD 98-09-23, amendment 39-10504 (63 FR 23382, April 29, 1998), applicable to certain Lockheed Model L- 1011 series airplanes equipped with Rolls Royce RB211-22B engines, to require various modifications and corrective actions to prevent a potential fire hazard from an undetected gearbox fire.

However, this proposed AD would not affect the current requirements of those previously issued AD's.

Explanation of Relevant Service Information

The FAA has reviewed and approved Lockheed Service Bulletin 093-77- 059, dated February 25, 1998, and Revision 1, dated February 2, 1999. The service bulletin describes procedures for modifications to the engine turbine cooling air panel at the flight engineer/second officer's console, pilot's caution and warning light panel on the main instrument panel, and monitoring system for the engine turbine air temperature. The modification to the engine turbine cooling air panel involves installation of a HSGB overheat (OVHT) marker. The modification to the pilot's caution and warning light panel on the main instrument panel involves renaming the pilot's caution and warning light panel ``TURB AIR OVHT ENG 1'' indicator light to ``TURB AIR / HSGB ENG 1'', ``TURB AIR OVHT ENG 2'' to ``TURB AIR / HSGB ENG 2,'' and ``TURB AIR OVHT ENG 3'' to ``TURB AIR / HSGB ENG 3.'' The modification to the monitoring system for the engine turbine air temperature involves installation of a revised breather duct assembly for the HSGB; installation of two overheat detectors in the gearbox breather duct assembly; wiring modifications to the fancase/A-frame to engine core services loom assembly; installation of a spiral anti-chafe sleeve over the modified fancase/A-frame; and installation of additional clipping brackets for the wiring modifications. Accomplishment of the actions specified in the service bulletin is intended to adequately address the identified unsafe condition.

Lockheed Service Bulletin 093-77-059 refers to Rolls Royce Service Bulletins RB.211-72-C178, dated March 20, 1998; and RB.211-77-C144, dated August 7, 1998; as additional sources of service information for accomplishment of the modification to the monitoring system for the engine turbine air temperature.

Explanation of Requirements of Proposed Rule

Since an unsafe condition has been identified that is likely to exist or develop on other products of this same type design, the proposed AD would require accomplishment of the actions specified in Lockheed Service Bulletin 093-77-059 described previously.

Cost Impact

There are approximately 235 airplanes of the affected design in the worldwide fleet. The FAA estimates that 117 airplanes of U.S. registry would be affected by this proposed AD, that it would take approximately 24 work hours per airplane to accomplish the proposed modifications, and that the average labor rate is $60 per work hour.

Required parts would cost approximately $6,350 per airplane. Based on these figures, the cost impact of the proposed AD on U.S. operators is estimated to be $911,430, or $7,790 per airplane.

The cost impact figure discussed above is based on assumptions that no operator has yet accomplished any of the proposed 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 proposed herein would not have substantial direct effects on the States, on the relationship between the national government and the States, or on the distribution of

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power and responsibilities among the various levels of government. Therefore, in accordance with Executive Order 12612, it is determined that this proposal would not have sufficient federalism implications to warrant the preparation of a Federalism Assessment.

For the reasons discussed above, I certify that this proposed regulation (1) is not a ``significant regulatory action'' under Executive Order 12866; (2) is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) if promulgated, 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 copy of the draft regulatory evaluation prepared for this action is contained in the Rules Docket. A copy of it may be obtained by contacting the Rules Docket at the location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration proposes to amend 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.

   Sec. 39.13 [Amended]

2. Section 39.13 is amended by adding the following new airworthiness directive:

   Lockheed: Docket 98-NM-314-AD.

   Applicability: All Model L-1011-385 series airplanes, 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 undetected fires originating within the high speed gearbox (HSGB) from breaching the HSGB case, which could result in engine damage and increased difficulty in extinguishing a fire, accomplish the following:

   Modification

   (a) Within 24 months after the effective date of this AD, accomplish the actions specified in paragraphs (a)(1), (a)(2), and (a)(3) of this AD, in accordance with Lockheed Service Bulletin 093- 77-059, dated February 25, 1998; or Revision 1, dated February 2, 1999.

   (1) Modify the engine turbine cooling air panel at the flight engineer/second officer's console.

   (2) Modify the pilot's caution and warning light panel on the main instrument panel.

   (3) Modify the monitoring system for the engine turbine air temperature.

   Note 2: Lockheed Service Bulletin 093-77-059 refers to Rolls Royce Service Bulletins RB.211-72-C178, dated March 20, 1998; and RB.211-77-C144, dated August 7, 1998; as additional sources of service information for accomplishment of the modification of the monitoring system for the engine turbine air temperature.

   Spares

   (b) As of the effective date of this AD, no person shall install on any airplane, an engine turbine cooling air panel assembly, part number 1559672, or a pilot's caution and warning light panel assembly on the main instrument panel, unless it has been modified in accordance with paragraphs (a)(1) and (a)(2) of this AD, as applicable.

   Alternative Methods of Compliance

   (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 Aircraft Certification Office (ACO), FAA, Small Airplane Directorate.

   Note 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Atlanta ACO.

   Special Flight Permits

   (d) Special flight permits may be issued in accordance with Secs. 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.

   Issued in Renton, Washington, on November 16, 1999. D.L. Riggin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.

   [FR Doc. 99-30371Filed11-19-99; 8:45 am]

   BILLING CODE 4910-13-P