[Federal Register Volume 63, Number 116 (Wednesday, June 17, 1998)]
[Proposed Rules]
[Pages 33019-33021]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-16022]


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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).

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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 filed in 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. 98-16022 Filed 6-16-98; 8:45 am]
BILLING CODE 4910-13-U