[Federal Register Volume 61, Number 152 (Tuesday, August 6, 1996)]
[Proposed Rules]
[Pages 40762-40764]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-19891]


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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 95-NM-248-AD]
RIN 2120-AA64


Airworthiness Directives; Lockheed Model 382 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 all Lockheed Model 382 series 
airplanes. This proposal would require that all landing gear brakes be 
inspected for wear and replaced if the wear limits prescribed in this 
proposal are not met, and that the new landing gear brake wear limits 
be incorporated into the FAA-approved maintenance inspection program. 
This proposal is prompted by an accident in which a transport category 
airplane executed a rejected takeoff (RTO) and was unable to stop on 
the runway due to worn brakes; and the subsequent review of allowable 
brake wear limits for all transport category airplanes. The actions 
specified by the proposed AD are intended to prevent

[[Page 40763]]

loss of brake effectiveness during a high energy RTO.

DATES: Comments must be received by September 16, 1996.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-103, 
Attention: Rules Docket No. 95-NM-248-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, Campus Building, 1701 Columbia Avenue, Suite 2-
160, College Park, Georgia 30337-2748.

FOR FURTHER INFORMATION CONTACT: Thomas Peters, Aerospace Engineer, 
Flight Test Branch, ACE-116A, FAA, Small Airplane Directorate, Atlanta 
Aircraft Certification Office, Campus Building, 1701 Columbia Avenue, 
Suite 2-160, College Park, Georgia 30337-2748; telephone (404) 305-
7367; fax (404) 305-7348.

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 95-NM-248-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-103, Attention: Rules 
Docket No. 95-NM-248-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    -In 1988, a McDonnell Douglas Model DC-10 series airplanes was 
involved in an aborted takeoff accident in which eight of the ten 
brakes failed and the airplane ran off the end of the runway. 
Investigation revealed that there were failed pistons on each of the 
eight brakes, with O-rings damaged by over-extension due to extensive 
wear. Fluid leaking from the damaged pistons caused the hydraulic fuses 
to close, releasing all brake pressure.
    -This accident prompted a review of the methodology used in the 
determination of the allowable wear limits for all transport category 
airplane brakes. The FAA and the Aerospace Industries Association (AIA) 
jointly developed a set of dynamometer test guidelines that could be 
used to validate appropriate wear limits for all airplane brakes. It 
should be noted that this worn brake accountability determination 
validates brake wear limits with respect to brake energy capacity only, 
and is not meant to account for any reduction in brake force due solely 
to the wear state of the brake. Any reduction in brake force (or 
torque) that may develop over time as a result of brake wear is to be 
evaluated and accounted for as part of a separate rulemaking project. 
The guidelines for validating brake wear limits allow credit for use of 
reverse thrust to determine energy level absorbed by the brake during 
the dynamometer test.
    -The FAA has requested that U.S. airframe manufacturers (1) 
Determine required adjustments in allowable wear limits for all of its 
brakes in use, (2) schedule dynamometer testing to validate wear limits 
as necessary, and (3) submit information from items (1) and (2) to the 
FAA so that appropriate rulemaking action(s) can be initiated.
    -Lockheed Aeronautical System Company has submitted, and the FAA 
has evaluated, the dynamometer test data and analyses concerning brakes 
installed on Model 382 series airplanes. The dynamometer test was 
completed in November 1990. Based on this data, the FAA has determined 
that the brake wear limits currently recommended in the Component 
Maintenance Manuals for Model 382 series airplanes are not acceptable 
as they relate to the effectiveness of the brakes during a high energy 
RTO. Further, these limits are only recommended values.

Explanation of Relevant Service Information

    -The FAA has reviewed and approved Hercules Alert Service Bulletin 
A382-32-47, dated March 1, 1995, which describes a new maximum brake 
wear limit approved by the FAA. The service bulletin describes 
procedures for performing an inspection of the main landing gear 
brakes, having part number 9560685, for wear. The service bulletin also 
describes procedures for replacement of any brake worn more than the 
maximum wear limit of 0.359 inch with a brake within that limit.
    -The FAA has determined that the actions described in this service 
bulletin must be taken in order to prevent loss of brake effectiveness 
during a high energy RTO, which can cause the airplane to leave the 
runway surface, possibly resulting in injuries to passengers and crew.

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 (1) inspection of the main landing gear 
brakes, having part number 9560685, for wear, and replacement if the 
new wear limits are not met; and (2) incorporation of specified maximum 
wear limits into the FAA-approved maintenance inspection program. The 
inspection and replacement would be required to be accomplished in 
accordance with the service bulletin described previously.

Cost Impact

    There are approximately 112 Lockheed Model 382 series airplanes of 
the affected design in the worldwide fleet. The FAA estimates that 18 
airplanes of U.S. registry would be affected by this proposed AD, that 
it would take approximately 1 work hour per airplane to accomplish the 
proposed actions, and that the average labor rate is $60 per work hour. 
The cost of parts to accomplish the change (cost resulting from the 
requirement to change the brakes before they are worn to their 
previously approved limits for a one-

[[Page 40764]]

time change) is estimated to be $4,800 per airplane. Based on these 
figures, the cost impact of the proposed AD on U.S. operators is 
estimated to be $87,480, or $4,860 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.''

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 95-NM-248-AD.

    Applicability: All Model 382 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 (b) 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 loss of brake effectiveness during a high energy 
rejected takeoff (RTO), accomplish the following:
    (a) Within 180 days after the effective date of this AD, 
accomplish the requirements of paragraphs (a)(1) and (a)(2) of this 
AD.
    (1) Inspect the main landing gear brakes having the brake part 
number listed below for wear, in accordance with Hercules Alert 
Service Bulletin A382-32-47, dated March 1, 1995. Any brake worn 
more than the maximum wear limit specified below must be replaced, 
prior to further flight, with a brake within that limit, in 
accordance with the alert service bulletin.

------------------------------------------------------------------------
                                                               Maximum  
              Brake manufacturer                 Brake part   wear limit
                                                  mumber-      (inches) 
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Hercules-.....................................     9560685-        0.359
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    (2) Incorporate into the FAA-approved maintenance inspection 
program the maximum brake wear limits specified in paragraph (a)(1) of 
this AD.
    (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, FAA, Small Airplane Directorate, Atlanta 
Aircraft Certification Office (ACO). 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 2: 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.

    Issued in Renton, Washington, on July 30, 1996.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 96-19891 Filed 8-5-96; 8:45 am]
BILLING CODE 4910-13-U