[Federal Register Volume 61, Number 115 (Thursday, June 13, 1996)]
[Proposed Rules]
[Pages 29996-30001]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-14988]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 95-NM-227-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300, A300-600, A310, and
A320 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: This document proposes the supersedure of an existing
airworthiness directive (AD), applicable to certain Airbus Model A300,
A300-600, A310, and A320 series airplanes, that currently requires an
inspection of the landing gear brakes for wear, and replacement if the
specified wear limits are not met. That AD also requires incorporation
of the specified wear limits into the FAA-approved maintenance
inspection program. This action would require that certain wear limits
that are dependent on brake stack weight be used in conjunction with
specified brake stack weights, and that maximum allowable
[[Page 29997]]
brake wear limits for additional brake units be incorporated into the
FAA-approved maintenance program. This proposal is prompted by a report
that some brakes that are subject to the requirements of the existing
AD have not been removed from service and by the determination of the
maximum allowable brake wear limits for additional brake unit part
numbers. The actions specified by the proposed AD are intended to
prevent the loss of brake effectiveness during a high energy rejected
takeoff.
DATES: Comments must be received by July 22, 1996.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 95-NM-227-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 Messier Services, 45635 Willow Pond Plaza, Sterling,
Virginia 20164; Allied Signal Aerospace, Technical Publications, Dept.
65-70, P.O. Box 52170, Phoenix, Arizona 85072-2170; or BFGoodrich
Company, Aircraft Evacuation Systems, Department 7916, Phoenix, Arizona
85040. This information may be examined at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton, Washington.
FOR FURTHER INFORMATION CONTACT: Joe Jacobsen, Aerospace Engineer,
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206)
227-2011; fax (206) 227-1149.
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-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. 95-NM-227-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
On December 14, 1994, the FAA issued AD 94-26-05, amendment 39-9101
(59 FR 65927, December 22, 1994), applicable to certain Airbus Model
A300, A300-600, A310, and A320 series airplanes, to require an
inspection of certain landing gear brakes for wear, and replacement if
the specified wear limits are not met. That AD also requires
incorporation of the specified wear limits into the FAA-approved
maintenance inspection program. That action was 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
subsequent review of allowable brake wear limits for all transport
category airplanes. The requirements of that AD are intended to prevent
the loss of brake effectiveness during a high energy RTO.
Actions Since Issuance of Previous Rule
Since the issuance of that AD, the airplane manufacturer and one
brake unit manufacturer have advised the FAA that certain brake part
numbers and maximum brake wear information provided to the FAA and
specified in AD 94-26-05 was incorrect and must be revised. The FAA
finds that this information must be revised in order to ensure that any
brake worn beyond its maximum wear limit is replaced with a brake
within that limit.
Additionally, the FAA has been advised that some brakes that are
subject to the requirements of AD 94-26-05 have not been removed from
service. These particular brakes are unable to withstand maximum RTO
energy with the wear pin limit specified in the existing AD due to
lower brake stack weights. Consequently, the FAA has determined that a
requirement that certain wear limits that are dependent on brake stack
weight must be used in conjunction with appropriate brake stack weights
specified in the brake manufacturer's Component Maintenance Manual
(CMM), certain service bulletins, or the Airplane Maintenance Manual.
Further, additional brake unit part numbers that were not addressed
in AD 94-26-05 have since been evaluated, and the maximum allowable
brake wear limits for these brake units have been determined in
accordance with a methodology approved by the FAA. The newly identified
maximum brake wear limits must be applied to these brake configurations
in order to ensure their braking effectiveness. The FAA has determined
that airplanes equipped with these brake units are currently subject to
the same unsafe condition addressed in the existing AD.
The FAA also finds that references to certain brake part numbers
that were specified in the existing AD must be clarified to indicate
that the listing refers to a ``series''of brake part numbers.
Additionally, the FAA has determined that certain service
information specified in the existing AD must be revised to specify
issuance dates and revision levels.
Type Certification of the Affected Airplanes
These airplane models are manufactured in France and are type
certificated for operation in the United States under the provisions of
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and
the applicable bilateral airworthiness agreement.
Explanation of Requirements of Proposed Rule
Since an unsafe condition has been identified that is likely to
exist or develop on other airplanes that are of the same type design,
that are equipped with the subject brake configurations, and that are
registered in the United States, the proposed AD would supersede AD 94-
26-05. This proposed AD would continue to require inspection of certain
landing gear brakes for wear, replacement of the brakes if certain wear
limits are not met, and incorporation of the specified wear limits into
the FAA-approved maintenance inspection program. Additionally, the
proposed AD would:
[[Page 29998]]
Revise certain brake part numbers and maximum brake wear
information specified in the existing AD;
Require that certain wear limits that are dependent on
brake stack weight be used in conjunction with appropriate brake stack
weights specified in various service documents; and
Require that maximum allowable brake wear limits for
additional brake units be incorporated into the FAA-approved
maintenance program.
Cost Impact
There are approximately 165 Model A300, A300-600, A310, and A320
series airplanes of U.S. registry that would be affected by this
proposed AD.
Incorporation of the revision of the FAA-approved maintenance
inspection program, which is currently required by AD 94-26-05, takes
approximately 20 work hours per operator (for 4 U.S. operators) to
accomplish, at an average labor rate of $60 per work hour. Based on
these figures, the cost impact on U.S. operators to accomplish this
currently required action is estimated to be $4,800, or $1,200 per
operator.
The inspection currently required by AD 94-26-05 takes
approximately 15 work hours per airplane to accomplish, at an average
labor rate of $60 per work hour. 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)
will be approximately $2,236 per airplane. The FAA estimates that 46 of
the 165 affected airplanes of U.S. registry will be required to
accomplish the inspection. Based on these figures, the cost impact on
U.S. operators to accomplish the currently required inspection is
estimated to be $144,256, or $3,136 per airplane.
The new actions that are proposed in this AD action would affect
one U.S. operator of 8 airplanes. The FAA estimates that the new
actions would take approximately 15 work hours per airplane to
accomplish, at an average labor rate of $60 per work hour. Required
parts would cost approximately $2,236 per airplane. Based on these
figures, the cost impact on the affected U.S. operator of the proposed
requirements of this AD is estimated to be $3,136 per airplane.
The cost impact figures discussed above are based on assumptions
that no operator has yet accomplished any of the current or 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 removing amendment 39-9101 (59 FR
65927, December 22, 1994), and by adding a new airworthiness directive
(AD), to read as follows:
Airbus Industrie: Docket 95-NM-227-AD. Supersedes AD 94-26-05,
Amendment 39-9101.
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.
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 (d) 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 the loss of brake effectiveness during a high energy
rejected takeoff (RTO), accomplish the following:
RESTATEMENT OF REQUIREMENTS OF AD 94-26-05
(a) Within 180 days after January 23, 1995 (the effective date
of AD 94-26-05, amendment 39-9101), accomplish paragraphs (a)(1) and
(a)(2) of this AD.
(1) Inspect main landing gear brakes having the brake part
numbers listed in Table 1, below, for wear. Any brake worn more than
the maximum wear limit specified in Table 1, below, must be
replaced, prior to further flight, with a brake within that limit.
Table 1
[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]
------------------------------------------------------------------------
Maximum brake
Airplane model/ Brake Brake part No.- wear limit (inch/
series- manufacturer- 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.*
A300 B4-100- Messier-Bugatti A21329-41-7- 1.1'' (28.0 mm).
[[Page 29999]]
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.*
A300 B4-100- BFGoodrich 2-1449 1.4'' (35.6 mm).
A300 B4-100- BFGoodrich 2-1449 1.1'' (27.9 mm)
S.C.*
A300 B4-200 Messier-Bugatti C20060-100- 1.1'' (28.0 mm).
and A300-600-
A300-600 ALS (Bendix) 2607932-1 0.9'' (22.9 mm).
A300-600 ALS (Bendix) 2607932-1 1.48'' (37.6 mm)
S.C.*
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.*
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 BFGoodrich 2-1526-2 1.97'' (50.0
mm).
A320 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 (CMM).
Note 2: Measuring instructions that must be revised to
accommodate the new brake wear limits specified in Table 1, 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
CMM, or in certain service bulletins (SB), as listed in Table 2,
below:
Table 2
------------------------------------------------------------------------
Date/revision
Brake Part No.-- Document/chapter (or later
manufacturer-- 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 and S.C.*- CMM 32-44-37 January 1993.
SB 567 (2-1449- January 30,
32-4)- 1993.
FOR MODEL A300 B4-100 SERIES AIRPLANES:
ALS (Bendix)- 2606802-3- CMM 32-42-02- September 1993.
2606802-4 SB 2606802-32- March 31, 1993.
2606802-5 and 003-
S.C.*-
BFGoodrich- 2-1449 and S.C.*- CMM 32-44-37 January 1993.
SB 567 (2-1449- January 30,
32-4)- 1993.
FOR MODEL A300 B4-200 AND A300-600 SERIES AIRPLANES:
ALS (Bendix)- 2607932-1 and CMM 32-42-27 September 1993.
S.C.*- SB 2607932-32- March 31,1993
002- and Revision 1/
October 1, 1993.
FOR MODEL A300 B4-600R SERIES AIRPLANES:
Messier-Bugatti- C20210000 Airbus SB 470-32- April 6, 1990.
and C20210200- 675-
FOR MODEL A310-200 SERIES AIRPLANES:
ALS (Bendix)- 2606822-1 & S.C.*- CMM 32-42-03 September 1993.
SB 2606822-32- March 31, 1993.
002 -
FOR MODEL A310-300 SERIES AIRPLANES:
Messier-Bugatti- C20225000 Airbus SB 470-32- April 6, 1990. --
and C20225200- 675-
------------------------------------------------------------------------
* S.C. represents ``Service Configured'' brakes, which are marked
according to the instructions provided in the brake manufacturer's
CMM.
(2) Incorporate into the FAA-approved maintenance inspection
program the maximum brake wear limits specified in paragraph (a)(1)
of this AD.
Note 3: Once an operator has complied with the requirements of
paragraphs (a)(1) and (a)(2) of this AD, those paragraphs do not
require that operators subsequently record accomplishment of those
requirements each time a brake is inspected or overhauled in
accordance with that operator's FAA-approved maintenance inspection
program.
[[Page 30000]]
NEW REQUIREMENTS OF THIS AD
(b) Within 90 days after the effective date of this AD, revise
the FAA-approved maintenance program to include the requirements of
paragraphs (b)(1), (b)(2), (b)(3), and (b)(4) of this AD.
Accomplishment of these requirements terminates the requirements of
paragraph (a) of this AD.
(1) Incorporate the maximum wear pin limits specified in Table 3
of this AD into the FAA-approved maintenance program.
(2) Comply with those measurements thereafter.
(3) Measure the brake wear in accordance with Chapter 32-42-27
of the AMM, with Chapter 32-32-( ) of the brake manufacturer's CMM,
or with certain service bulletins (SB), as listed in Table 4, below.
Brake wear limits specified in Table 3, below, that are identified
in the service information specified in Table 4, below, as being
dependent on brake stack weights shall be used in conjunction with
the brake stack weights specified in that service information.
(4) If any brake has measured wear beyond the maximum wear
limits specified in Table 3 of this AD, prior to further flight,
replace it with a brake that is within the wear limits specified in
Table 3.
Table 3
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
------------------------------------------------------------------------
Maximum brake
Airplane model/ Brake Brake part No.- wear limit (inch/
series- manufacturer- 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.*
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/-200- ALS (Bendix)- 2606802-3/-4/-5 0.9'' (22.9 mm).
A300 B4-100/-200- ALS (Bendix)- 2606802-3/-4/-5 1.48'' (37.6 mm)
S.C.*
A300-B4-100- BFGoodrich- 2-1449- 1.4'' (35.6 mm).
A300-B4-100- BFGoodrich- 2-1449- 1.1'' (27.9 mm)
S.C.*
A300-600- Messier-Bugatti- C20060-100 1.1'' (28.0 mm).
Series-
A300-600- ALS (Bendix)- 2607932-1- 0.9'' (22.9 mm).
A300-600- ALS (Bendix)- 2607932-1- 1.48'' (37.6 mm)
S.C.*
A300 B4-600R Messier-Bugatti- C20210000 Series- 1.97'' (50.0
mm). -
A300 B4-600R- Messier-Bugatti- C20210200 Series- 1.97'' (50.0
mm). -
A310-200- Messier-Bugatti- C20089000 Series- 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.*
A310-300- Messier-Bugatti- C20194000 Series 1.97'' (50.0
- mm). -
A310-300- Messier-Bugatti- C20194200 Series 1.97'' (50.0
- mm). -
A310-300- ABS- 5010995- 2.22'' (56.39
mm).
A320- Messier-Bugatti- C20225000 Series- 1.97'' (50.0
mm).
A320- Messier-Bugatti- C20225200 Series- 1.97'' (50.0
mm). -
A320- BFGoodrich- 2-1526- 1.97'' (50.0
mm).
A320- BFGoodrich- 2-1526-2- 1.97'' (50.0
mm).
A320- BFGoodrich- 2-1526-5- 1.97'' (50.0
mm).
A320- BFGoodrich- 2-1526-3/-4- 2.68'' (68.0
mm).
A320- BFGoodrich- 2-1572- 2.68'' (68.0
mm).
A320- ABS- 5011075- 2.14'' (54.36
mm).
------------------------------------------------------------------------
* S.C. represents ``Service Configured'' brakes, which are marked
according to the instructions provided in the brake manufacturer's
CMM.
Table 4
------------------------------------------------------------------------
Date/revision
Brake Part No. Document/chapter (or later
manufacturer revisions)
------------------------------------------------------------------------
FOR MODEL A300 B2-100 SERIES AIRPLANES:
Messier-Bugatti 286349-115 CMM 32-42-27- April 30, 1991.
Messier-Bugatti 286349-116 CMM 32-42-27- April 30, 1991.
BFGoodrich 2-1449 and S.C.* CMM 32-44-37 January 30,
SB 567 (2-1449- 1993.
32-4)- January 30,1993.
FOR MODEL A300 B4-100 SERIES AIRPLANES:
Messier-Bugatti A21329-41-17 CMM 32-44-37 January 30,
1993.
ALS (Bendix) 2606802-3 CMM 32-42-02 Revision 7/April
2606802-4 SB 2606802-32- 30, 1995.
2606802-5 and 003 March 31, 1993,
S.C.* and
Revision 1/
October 1,
1993.
BFGoodrich- 2-1449 and S.C.* CMM 32-44-37 January 30,
SB 567 (2-1449- 1993.
32-4)- - January 30,
1993.
FOR MODEL A300 B4-200 SERIES AIRPLANES:
Messier-Bugatti C20060-100 Series CMM 32-44-24 December 31,
1991.
ALS (Bendix) 2606802-3 CMM 32-42-02 Revision 7/April
2606802-4 SB 2606802-32- 30, 1995.
2606802-5 and 003 March 31, 1993,
S.C.* and
Revision 1/
October 1,
1993.
[[Page 30001]]
FOR MODEL A300-600 SERIES AIRPLANES:
Messier-Bugatti C20060-100 Series CMM 32-44-24 December 31,
1991.
ALS (Bendix) 2607932-1 and CMM 32-42-05 Revision 4/
S.C.* SB 2607932-32- February
002 15,1992.
SB 2607932-32- March 31,1993,
003 and
Revision 1/
October 1,
1993.
May 31, 1995.
- - FOR MODEL A300 B4-600R SERIES AIRPLANES:
Messier-Bugatti C20210000 CMM 32-44-51 August 31, 1994.
and SB 470-32-675 Revision 1/
C20210200 Series September 26,
1994.
--FOR MODEL A310-200 SERIES AIRPLANES:
Messier-Bugatti C20089000 Series CMM 32-46-23 January 31,
1992.
ALS (Bendix) 2606822-1 and CMM 32-42-03 Revision 5/
S.C. January 31,
SB 2606822-32- 1991.
002 - March 31, 1993.
--FOR MODEL A310-300 SERIES AIRPLANES:
Messier-Bugatti C20194000 and CMM 32-46-37 August 31, 1994.
C20194200 Series SB 470-32-675 Revision 1/
September 26,
1994.
ABS 5010995 CMM 32-43-97 February 28,
1991.
FOR MODEL A320 SERIES AIRPLANES:
Messier-Bugatti C20225000 and CMM 32-47-20 January 31,
C20225200 Series SB 580-32-3042 1995.
Revision 1/June
30, 1995. ---
BFGoodrich 2-1526/-2/-5 CMM 32-44-38 March 15, 1993.
2-1526-3/-4 CMM 32-44-38 March 15, 1993.
2-1572 CMM 32-41-63 April 29, 1994.
ABS 5011075 CMM 32-41-18 February 28,
1991.
------------------------------------------------------------------------
* S.C. represents ``Service Configured'' brakes, which are marked
according to the instructions provided in the brake manufacturer's
CMM.
NOTE 4: Once an operator has complied with the requirement of
paragraph (b) of this AD, that paragraph does not require that the
operator subsequently record accomplishment of those requirements
each time a brake is inspected or overhauled in accordance with that
operator's FAA-approved maintenance inspection program.
(c) Prior to installation of any brake having a part number
other than those specified in Table 3 of this AD, revise the FAA-
approved maintenance program to include the provisions specified in
paragraph (b) of this AD for that part number brake, that have been
approved by the Manager, Standardization Branch, ANM-113, FAA,
Transport Airplane Directorate.
-(d) 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.
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 5: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Standardization Branch, ANM-113.
-(e) 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 6, 1996.
James V. Devany,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 96-14988 Filed 6-12-96; 8:45 am]
BILLING CODE 4910-13-U