Airworthiness directives: Lockheed,

[Federal Register: June 17, 1998 (Volume 63, Number 116)]

[Proposed Rules]

[Page 33019-33021]

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

[DOCID:fr17jn98-22]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-36-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 certain Lockheed Model L-1011-385 series airplanes. This proposal would require the replacement of the flap position indicator with an improved flap position indicator. This proposal is prompted by a report indicating that an airplane landed at an excessive sink rate and sustained substantial structural

[[Page 33020]]

damage when the leading edge slats failed to extend for landing and the flightcrew failed to increase airspeed in response, due to inadequate annunciation of the slat failure. The actions specified by the proposed AD are intended to prevent such inadequate annunciation, which could result in the flightcrew being unaware when the leading edge slats fail to extend properly; such failure could result in reduced stall margins, and consequent reduced controllability of the airplane.

DATES: Comments must be received by August 3, 1998.

ADDRESSES: Submit comments in triplicate to the Federal Aviation Administration (FAA), Transport Airplane Directorate, ANM-114, Attention: Rules Docket No. 98-NM-36-AD, 1601 Lind Avenue, SW., Renton, Washington 98055-4056. Comments may be inspected at this location between 9:00 a.m. and 3:00 p.m., Monday through Friday, except Federal holidays.

The service information referenced in the proposed rule 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 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, Program Manager, 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 30337-2748; 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-36-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-36-AD, 1601 Lind Avenue, SW., Renton, Washington 98055-4056.

Discussion

The FAA has received a report indicating that the flightcrew of a Lockheed Model L-1011-385 series airplane failed to notice that the leading edge slats did not extend during approach for landing. As a result, the approach speed was not adjusted to compensate for this abnormal configuration. The airplane landed at an excessive sink rate and sustained substantial structural damage. The cause has been attributed to the existing design of the flap and slat display system, which does not provide adequate annunciation to the flightcrew when the leading edge slats have failed to extend. The existing flap position indicator of the flap and slat display system does not provide a conspicuous warning should the leading edge slats fail to extend or retract properly during flap operation. This condition, if not corrected, could result in the flightcrew being unaware when the leading edge slats fail to extend properly; such failure could result in reduced stall margins, and consequent reduced controllability of the airplane.

Explanation of Relevant Service Information

The FAA has reviewed and approved Lockheed Service Bulletin 093-27- 128, Revision 2, dated December 1, 1997, which describes procedures for replacement of the flap position indicator with an improved flap position indicator. Accomplishment of the actions specified in the service bulletin is intended to adequately address the identified unsafe condition.

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 action specified in the service bulletin described previously.

Cost Impact

There are approximately 164 airplanes of the affected design in the worldwide fleet. The FAA estimates that 89 airplanes of U.S. registry would be affected by this proposed AD, that it would take approximately 2 work hours per airplane to accomplish the proposed replacement, and that the average labor rate is $60 per work hour. Required parts would cost approximately $25,000 per airplane. Based on these figures, the cost impact of the replacement proposed by this AD on U.S. operators is estimated to be $2,235,680, or $25,120 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 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.

[[Page 33021]]

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-36-AD.

    Applicability: Model L-1011-385-1, -14, and -15 series airplanes, as listed in Lockheed Service Bulletin 093-27-128, Revision 2, dated December 1, 1997; 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 inadequate annunciation to the flightcrew of leading edge slat failures, which could result in reduced stall margins, and consequent reduced controllability of the airplane, accomplish the following:

    (a) Within 18 months after the effective date of this AD, replace the flap position indicator with a new, improved flap position indicator, in accordance with Lockheed Service Bulletin 093-27-128, Revision 2, dated December 1, 1997.

    Note 2: Replacement of the flap position indicator accomplished prior to the effective date of this AD, in accordance with Lockheed Service Bulletin 093-27-128, dated November 8, 1976, or Revision 1, dated January 17, 1977, is considered acceptable for compliance with paragraph (a) of this AD.

    (b) As of the effective date of this AD, no person shall install a flap position indicator, part number 672563-111 or 672563-115, on any airplane.

    (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.

    Issued in Renton, Washington, on June 9, 1998. John J. Hickey, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.

    [FR Doc. 98-16022Filed6-16-98; 8:45 am]

    BILLING CODE 4910-13-U

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