[Federal Register Volume 59, Number 31 (Tuesday, February 15, 1994)]
[Unknown Section]
[Page 0]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 94-3461]
[[Page Unknown]]
[Federal Register: February 15, 1994]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 93-NM-227-AD]
Airworthiness Directives; Airbus Industrie Model A300, A300-600,
A310, and A320 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 Airbus Industrie Model
A300, A300-600, A310, and A320 series airplanes. This proposal would
require that certain landing gear brakes be inspected for wear and
replaced if the wear limits prescribed in this proposal are not met,
and that the specified 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 the loss of brake effectiveness during a high
energy RTO.
DATES: Comments must be received by April 11, 1994.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 93-NM-227-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.
FOR FURTHER INFORMATION CONTACT: Mark Quam, Aerospace Engineer,
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206)
227-2145; fax (206) 227-1320.
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 93-NM-227-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. 93-NM-227-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion -
In 1988, a McDonnell Douglas Model DC-10 series airplane 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 allowable wear limits for all
brakes installed on transport category airplanes. 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.
The guidelines for validating brake wear limits allow credit for use of
reverse thrust with a critical engine inoperative to determine the
energy level absorbed by the brake during the dynamometer test. -
The FAA has requested that airframe manufacturers of transport
category airplanes: (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. -
Airbus Industrie has conducted worn brake rejected takeoff (RTO)
dynamometer testing and analyses on various brakes installed on certain
Model A300, A300-600, A310, and A320 series airplanes. Based on the
results of that testing and analyses, the FAA has determined that the
maximum brake wear limits currently recommended in the Component
Maintenance Manual for Model A300, A300-600, A310, and A320 series
airplanes equipped with brakes manufactured by Messier-Bugatti,
BFGoodrich, Allied Signal (ALS) Aerospace Company (Bendix), or Aircraft
Braking Systems (ABS) are acceptable as they relate to the
effectiveness of the brakes during a high energy RTO. Consequently, the
FAA has determined that the brake wear limits for Model A300, A300-600,
A310, and A320 series airplanes must be incorporated into the FAA-
approved maintenance inspection program. -
The FAA has determined that, in order to prevent loss of brake
effectiveness during a high energy RTO, the following maximum brake
wear limits are necessary for Model A300, A300-600, A310, and A320
series airplanes equipped with Messier-Bugatti, BFGoodrich, ALS
Aerospace Company (Bendix), or ABS brakes.
Airbus Industrie Model A300, A300-600, A310, And A320 Series Airplanes Equipped With Messier-Bugatti, BFGoodrich, Allied Signal (ALS) Aerospace Company
(Bendix), or Aircraft Braking Systems (ABS) Brakes
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Airplane model/series Brake manufacturer Brake part No. Maximum brake wear limit (inch/mm)
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A300-B2-100-............................ Messier-Bugatti........................ 286349-115 0.98'' (25.0 mm).
A300-B2-100............................. Messier-Bugatti........................ 286349-116-- 0.98'' (25.0 mm).
A300-B2-100-............................ BFGoodrich-............................ 2-1449-- 1.4'' (35.6 mm).
A300-B2-100-............................ BFGoodrich-............................ 2-1449-- 1.1'' (27.9 mm) S.C.\1\
A300-B4-100-............................ Messier-Bugatti........................ A21329-41-7-- 1.1'' (28.0 mm).
A300-B4-100-............................ Messier-Bugatti........................ A21329-41-17- 1.1'' (28.0 mm).
A300-B4-100-............................ ALS (Bendix)-.......................... 2606802-3/-4/-5- 0.9'' (22.9 mm).
A300-B4-100-............................ ALS (Bendix)-.......................... 2606802-3/-4/-5- 1.48'' (37.6 mm) S.C.\1\
A300-B4-100-............................ BFGoodrich-............................ 2-1449-- 1.4'' (35.6 mm).
A300-B4-100-............................ BFGoodrich-............................ 2-1449-- 1.1'' (27.9 mm) S.C.\1\----------
A300-B4-200 & A300-600.................. Messier-Bugatti........................ C20060-100 1.1'' (28.0 mm).
A300-B4-200 & A300-600.................. ALS (Bendix)........................... 2607932-1 0.9'' (22.9 mm).
A300-B4-200 & A300-600.................. ALS (Bendix)........................... 2607932-1 1.48'' (37.6 mm) S.C.\1\
A300-B4-600R............................ Messier-Bugatti........................ C20210000- 1.97'' (50.0 mm).
A300-B4-600R............................ Messier-Bugatti........................ C20210200- 1.97'' (50.0 mm).
A310-200................................ Messier-Bugatti........................ C20089000 1.1'' (28.0 mm).
A310-200-............................... ALS (Bendix)-.......................... 2606822-1- 1.26'' (32.0 mm).
A310-200-............................... ALS (Bendix)-.......................... 2606822-1- 1.5'' (38.2 mm) S.C.\1\
A310-300 -.............................. Messier-Bugatti........................ C20194000- 1.97'' (50.0 mm).
A310-300-............................... Messier-Bugatti........................ C20194200- 1.97'' (50.0 mm).
A310-300-............................... ABS--.................................. 5010995- 1.97'' (50.0 mm).
A320-................................... Messier-Bugatti........................ C20225000- 1.97'' (50.0 mm).
A320-................................... Messier-Bugatti........................ C20225200- 1.97'' (50.0 mm).
A320-220-............................... BFGoodrich-............................ 2-1526-2- 1.97'' (50.0 mm).
A320-200-............................... BFGoodrich-............................ 2-1526-3/-4 2.68'' (68.0 mm).
--------------------------------------------------------------------------------------------------------------------------------------------------------
S.C. represents ``Service Configured'' brakes, which are marked according to the instructions provided in the brake manufacturer's Component Maintenance
Manual.
These airplanes are manufactured in France and are type
certificated for operation in the United States under the provisions of
Sec. 21.29 of the Federal Aviation Regulations and the applicable
bilateral airworthiness agreement. The FAA has determined that AD
action is necessary for products of this type design that are
certificated for operation in the United States.
Since an unsafe condition has been identified that is likely to
exist or develop on other airplanes of the same type design registered
in the United States, the proposed AD would require that certain
landing gear brakes be inspected for wear and replaced if the wear
limits prescribed in this proposal are not met, and that the specified
wear limits be incorporated into the FAA-approved maintenance
inspection program.
The FAA estimates that 101 Model A300, A300-600, A310, and A320
series airplanes of U.S. registry and 5 U.S. operators would be
affected by this proposed AD. The FAA estimates that it would take
approximately 20 work hours per operator, at an average labor rate of
$55 per work hour, for each operator to incorporate the proposed
revision of its FAA-approved maintenance inspection program. The total
cost impact of that proposed requirement on U.S. operators of Model
A300, A300-600, A310, and A320 series airplanes is estimated to be
$5,500, or $1,100 per operator.
The FAA also estimates that it would take 15 work hours per
airplane, at an average labor rate of $55 per work hour, to accomplish
the proposed inspection. The cost of required parts to accomplish the
change in wear limits for these airplanes (that is, the cost resulting
from the requirement to change the brakes before they are worn to their
previously approved limits for a one-time change) would be
approximately $2,236 per airplane. The FAA estimates that 28 of the 101
affected airplanes of U.S. registry would be required to accomplish the
proposed inspection. Based on these figures, the total cost impact of
that proposed requirement on U.S. operators of these airplanes is
estimated to be $85,708, or $3,061 per airplane.
These total cost figures assume that no operator has yet
accomplished the requirements of this AD.
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 14
CFR part 39 of the Federal Aviation Regulations as follows:
PART 39--AIRWORTHINESS DIRECTIVES-
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. App. 1354(a), 1421 and 1423; 49 U.S.C.
106(g); and 14 CFR 11.89.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
Airbus Industrie: Docket 93-NM-227-AD.
Applicability: Model A300, A300-600, A310, and A320 series
airplanes equipped with Messier-Bugatti, BFGoodrich, Allied Signal
(ALS) Aerospace Company (Bendix), or Aircraft Braking Systems (ABS)
brakes; certificated in any category.
Compliance: Required as indicated, unless accomplished
previously.
To prevent the 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 paragraphs (a)(1) and (a)(2) of this AD.
(1) Inspect main landing gear brakes having the brake part
numbers listed below for wear. Any brake worn more than the maximum
wear limit specified below must be replaced, prior to further
flight, with a brake within that limit.
Airbus Industrie Model A300, A300-600, A310, and A320 Series Airplanes Equipped with Messier-Bugatti, BFGoodrich, Allied Signal (ALS) Aerospace Company
(Bendix), or Aircraft Braking Systems (ABS) Brakes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Airplane model/series Brake manufacturer Brake part No. Maximum brake wear limit (inch/mm).
--------------------------------------------------------------------------------------------------------------------------------------------------------
A300-B2-100--........................... Messier-Bugatti-....................... 286349-115 0.98'' (25.0 mm).
A300-B2-100--........................... Messier-Bugatti-....................... 286349-116 0.98'' (25.0 mm).
A300-B2-100--........................... BFGoodrich--........................... 2-1449 1.4'' (35.6 mm).
A300-B2-100--........................... BFGoodrich--........................... 2-1449-- 1.1'' (27.9 mm). S.C.\1\
A300-B4-100--........................... Messier-Bugatti-....................... A21329-41-7-- 1.1'' (28.0 mm).
A300-B4-100--........................... Messier-Bugatti-....................... A21329-41-17- 1.1'' (28.0 mm).
A300-B4-100--........................... ALS (Bendix)-.......................... 2606802-3/-4/-5- 0.9'' (22.9 mm).
A300-B4-100--........................... ALS (Bendix)-.......................... 2606802-3/-4/-5- 1.48'' (37.6 mm). S.C.\1\----------
A300-B4-100--........................... BFGoodrich--........................... 2-1449-- 1.4'' (35.6 mm).
A300-B4-100--........................... BFGoodrich--........................... 2-1449-- 1.1'' (27.9 mm). S.C.\1\
A300-B4-200 & A300-600.................. Messier-Bugatti-....................... C20060-100-- 1.1'' (28.0 mm).
A300-B4-200 & A300-600.................. ALS (Bendix)-.......................... 2607932-1-- 0.9'' (22.9 mm).
A300-B4-200 & A300-600.................. ALS (Bendix)-.......................... 2607932-1-- 1.48'' (37.6 mm). S.C.\1\
A300-B4-600R-........................... Messier-Bugatti-....................... C20210000-- 1.97'' (50.0 mm).
A300-B4-600R-........................... Messier-Bugatti-....................... C20210200-- 1.97'' (50.0 mm).
A310-200--.............................. Messier-Bugatti-....................... C20089000-- 1.1'' (28.0 mm).
A310-200--.............................. ALS (Bendix)-.......................... 2606822-1-- 1.26'' (32.0 mm).
A310-200--.............................. ALS (Bendix)-.......................... 2606822-1-- 1.5'' (38.2 mm). S.C.\1\
A310-300--.............................. Messier-Bugatti-....................... C20194000-- 1.97'' (50.0 mm).
A310-300--.............................. Messier-Bugatti-....................... C20194200-- 1.97'' (50.0 mm).
A310-300--.............................. ABS---................................. 5010995-- 1.97'' (50.0 mm).
A320---................................. Messier-Bugatti-....................... C20225000-- 1.97'' (50.0 mm).
A320---................................. Messier-Bugatti-....................... C20225200-- 1.97'' (50.0 mm).
A320-220--.............................. BFGoodrich--........................... 2-1526-2-- 1.97'' (50.0 mm).
A320-200--.............................. BFGoodrich--........................... 2-1526-3/-4- 2.68'' (68.0 mm).
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\1\S.C. represents ``Service Configured'' brakes, which are marked according to the instructions provided in the brake manufacturer's Component
Maintenance Manual.
Note 1: Measuring instructions that must be revised to
accommodate the new brake wear limits specified above can be found
in Chapter 32-42-27 of the Airplane Maintenance Manual (AMM), in
Chapter 32-32-( ) or 32-44-( ) of the brake manufacturer's Component
Maintenance Manual (CMM), or in certain service bulletins (SB), as
listed below:
----------------------------------------------------------------------------------------------------------------
Date/revision (or later
Brake manufacturer Part No. Document/chapter revisions)
----------------------------------------------------------------------------------------------------------------
For model A300-B2-100 series
airplanes:
Messier-Bugatti-............. 286349-115 CMM 32-42-27.............. April 1991.
Messier-Bugatti-............. 286349-116 CMM 32-42-27.............. April 1991.
BFGoodrich--................. 2-1449 & S.C.- CMM 32-44-37-............. January 1993.
........................ SB 567 (2-1449-32-4)...... January 30, 1993
For model A300-B4-100 series
airplanes:
ALS (Bendix)--............... 2606802-3-- CMM 32-42-02-............. September 1993.
2606802-4 SB 2606802-32-003......... March 31, 1993. ----
2606802-5 & S.C.
BFGoodrich................... 2-1449 & S.C. CMM 32-44-37.............. January 1993.
........................ SB 567 (2-1449-32-4)...... January 30, 1993.
For model A300-B4-200 and A300-
600 series airplanes:
ALS (Bendix)................. 2607932-1 & S.C. CMM 32-42-27.............. September 1993.
........................ SB 2607932-32-002......... March 31,1993 & Revision
1, dated October 1,
1993.
For model A300-B4-600R Series
Airplanes:
Messier-Bugatti-............. C20210000 & C20210200- Airbus SB 470-32-675...... April 6, 1990.
For model A310-200 series
airplanes:
ALS (Bendix)................. 2606822-1 & S.B. CMM 32-42-03.............. September 1993. ---- --
........................ SB 2606822-32-002......... March 31, 1993.
For model A310-300 Series
Airplanes:
Messier-Bugatti-............. C20225000 & C20225200-- Airbus SB 470-32-675...... April 6, 1990.
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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, Standardization Branch, ANM-113, FAA,
Transport 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, Standardization Branch, ANM-
113.
Note: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Standardization Branch, ANM-113.
(c) Special flight permits may be issued in accordance with Federal
Aviation Regulations (FAR) 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 February 9, 1994.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 94-3461 Filed 2-14-94; 8:45 am]
BILLING CODE 4910-13-U