[Federal Register Volume 62, Number 14 (Wednesday, January 22, 1997)]
[Rules and Regulations]
[Pages 3204-3209]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-810]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 95-NM-227-AD; Amendment 39-9888; AD 97-02-04]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300, A300-600, A310, and
A320 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment supersedes 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
amendment requires that certain wear limits that are dependent on brake
stack weight be used in conjunction with specified brake stack weights,
and that maximum allowable brake wear limits for additional brake units
be incorporated into the FAA-approved maintenance program. This
amendment 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 this AD
are intended to prevent the loss of brake effectiveness during a high
energy rejected takeoff.
EFFECTIVE DATE: February 26, 1997.
ADDRESSES: The service information that pertains to this rulemaking
action 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 Federal
Aviation Administration (FAA), Transport Airplane Directorate, Rules
Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of
the Federal Register, 800 North Capitol Street, NW., suite 700,
Washington, DC.
FOR FURTHER INFORMATION CONTACT: Joe Jacobsen, Aerospace Engineer,
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton,
[[Page 3205]]
Washington 98055-4056; telephone (206) 227-2011; fax (206) 227-1149.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) by superseding AD 94-26-05,
amendment 39-9101 (59 FR 65927, December 22, 1994), which is applicable
to certain Airbus Model A300, A300-600, A310, and A320 series
airplanes, was published in the Federal Register on June 13, 1996 (61
FR 29996). The action proposed to 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 action proposed to:
1. Revise certain brake part numbers and maximum brake wear
information specified in the existing AD;
2. 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
3. Require that maximum allowable brake wear limits for additional
brake units be incorporated into the FAA-approved maintenance program.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the comments received.
Support for the Proposal
Several commenters support the proposed rule.
Request for Clarification of Information in TABLE 3
One commenter states that certain information in TABLE 3 of the
proposal needs clarification to add the following information:
1. Messier-Bugatti C20060-100 series brakes can also be installed
on Airbus Model A300B4-200 series airplanes; however, TABLE 3 indicates
only the Model A300-600 as having these brakes installed.
2. Messier Bugatti C20175100 series brakes should be included as
brakes that can be installed on Model A300-600 series airplanes.
3. Messier-Bugatti C20210500 series brakes should be included as
brakes that can be installed on Model A300 B4-600R series airplanes.
The commenter points out that these brake models (and their
applicable brake wear limits) are included in the referenced
manufacturer's Component Maintenance Manual (CMM), but TABLE 3 did not
make it clear which airplane models are equipped with them.
The FAA concurs with the commenters observations and has made the
appropriate revisions to both TABLE 3 and TABLE 4 accordingly.
Request to Increase Wear Pin Length for Modified Brakes
One commenter requests that the proposal be revised to increase the
allowable wear pin length for Messier Bugatti C20210200 series brakes
from 1.97 inches to 2.559 inches by installation of a shim at the
thrust plate. The commenter states that this provision is contained in
Messier Service Bulletin 470-32-675, Revision 1, dated September 26,
1994 (which is cited in TABLE 4 under the brake wear limit references
for Model A300 B4-600R series airplanes).
The FAA does not concur. The FAA contacted the manufacturer, who
clarified this provision: When the shim is added, the total wear of the
heat pack is increased. However, the wear pin limit of 1.97 inches does
not change. In light of this, the FAA finds that the wear limit of 1.97
inches, as indicated in the notice, is correct.
Request for Addition of Wear Limits for Brakes with Carbon /D3/
Heat Packs
One commenter requests that the proposal be revised to specify what
the wear limits are for brakes equipped with the latest version of
Messier carbon /D3/ heat packs.
The FAA does not concur that a revision is necessary. The
manufacturer has advised the FAA that, contrary to what was previously
assumed, some /D3/ heat packs are still in service. However, the
manufacturer confirmed that the allowable wear limits specified in the
notice are independent of whether or not a /D3/ heat pack is used. The
wear limits, as stated in the notice, are correct.
Request to Clarify Requirement to Incorporate TABLE 3 Information
One commenter expresses confusion concerning the requirements of
proposed paragraph (b)(1), which appears to indicate that the entirety
of TABLE 3 must be incorporated into the FAA-approved maintenance
program, regardless of the type of airplane an operator may operate or
the type of brakes used. The commenter requests that this be clarified.
The FAA concurs that clarification may be necessary. In presenting
the information in the form of a table, the FAA assumed that operators
would incorporate into their programs only the specific information
pertaining to the airplanes that they actually operate, rather than all
of the information contained in TABLE 3. The table format was selected
as a more convenient method of displaying this information, rather than
designating individual paragraphs applicable to each individual
airplane model and/or brake models. Regardless of the format in which
this information is introduced, operators are required to comply only
with those items that directly affect the equipment that they operate.
The FAA has revised the wording of paragraph (b)(1) of the final rule
to make this more precise.
Request to Clarify Provisions Regarding Brake Stack Weights
One commenter requests that proposed paragraph (b)(3) be clarified
with regard to its specific requirements. That paragraph states first
that the brake wear is to be measured in accordance with certain
documents; it then states that listed brake wear limits that are
identified in referenced service documents as being dependent on brake
stack weights ``shall be used in conjunction with the brake stack
weights specified in that service information.'' The commenter
considers this to be ``impossible to understand.''
The FAA concurs that clarification may be appropriate. The purpose
of paragraph (b)(3) is to direct operators to service information that
provides specific procedures for measuring the brake wear of each type
of brake addressed in this AD. As indicated in that paragraph, these
procedural instructions are contained in the following sources:
1. Chapter 32-42-27 of the Airplane Maintenance Manual;
2. Chapter 32-32-( ) of the brake manufacturers Component
Maintenance Manual; and/or
3. Service bulletins listed in TABLE 4 of this AD.
The second sentence of paragraph (b)(3) addresses particular brakes
that, because of their lower (brake stack) weight, have proven to be
unable to withstand maximum rejected takeoff (RTO) energy when they are
fully worn to the limit that is specified in the previously issued AD.
If any of the service bulletins listed in TABLE 4 indicates that the
brake wear limit for a specific brake is dependent on the brake stack
weight of that brake, then the operator must verify that the brake wear
limit specified in TABLE 3 is being used with the correct brake stack
weight. The FAA points to an incident that occurred previously in which
the brake wear limit specified in the previously issued AD was used
with an incorrect brake
[[Page 3206]]
stack weight. This situation presented an unsafe condition because the
brake wear limit being used was beyond what the particular brake
actually should have been limited to in order to maintain braking
effectiveness during a high energy RTO. The wording of paragraph (b)(3)
is an attempt to prevent that error from occurring again.
The FAA has revised the wording of paragraph (b)(3) in this final
rule to clarify the intent of that paragraph.
Conclusion
After careful review of the available data, including the comments
noted above, the FAA has determined that air safety and the public
interest require the adoption of the rule with the changes previously
described. The FAA has determined that these changes will neither
increase the economic burden on any operator nor increase the scope of
the AD.
Cost Impact
There are approximately 165 Model A300, A300-600, A310, and A320
series airplanes of U.S. registry that will 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 required in this AD action will affect 1
U.S. operator of 8 airplanes. The FAA estimates that the new actions
will take approximately 15 work hours per airplane to accomplish, at an
average labor rate of $60 per work hour. Required parts will cost
approximately $2,236 per airplane. Based on these figures, the cost
impact on the affected U.S. operator of the 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 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 adopted herein will 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 final
rule does not have sufficient federalism implications to warrant the
preparation of a Federalism Assessment.
For the reasons discussed above, I certify that this action (1) is
not a ``significant regulatory action'' under Executive Order 12866;
(2) is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and (3) 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 final evaluation has been prepared for this action
and it is contained in the Rules Docket. A copy of it may be obtained
from 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.
Adoption of the Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration amends 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), amendment 39-9888, to read as follows:
97-02-04 Airbus Industrie: Amendment 39-9888. 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 wear limit
Airplane model/series Brake manufacturer Brake part No. (inch/mm)
----------------------------------------------------------------------------------------------------------------
A300 B2-100................. Messier-Bugatti 286349-115 0.98''(25.0 mm).
[[Page 3207]]
A300 B2-100................. Messier-Bugatti 286349-115 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 B2-100................. 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.*
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).
A300-600.................... Messier-Bugatti C20060-100 1.1''(28.0 mm).
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 (or
Brake manufacturer Part No. Document/Chapter later 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.
BF Goodrich.................. 2-1449 and 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, 2606802- SB 2606802- 32-003................ March 31, 1993.
5, and S.C.*.
BF Goodrich.................. 2-1449 and 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 and S.C.*. CMM 32-42-27...................... September 1993.
SB 2607932-32-002................. March 31,1993, and
Revision \1\
October 1, 1993.
For Model A300 B4-600R Series
Airplanes:
Messier-Bugatti.............. C20210000 and Airbus SB 470-32-675.............. April 6, 1990.
C20210200.
For Model A310-200 Series
Airplanes:
ALS (Bendix)................. 2606822-1 and S.C.*. CMM 32-42-03...................... September 1993.
SB 2606822-32-002................. March 31, 1993.
For Model A310-300 Series
Airplanes:
Messier-Bugatti.............. C20225000 and Airbus SB 470-32-675.............. April 6, 1990.
C20225200.
----------------------------------------------------------------------------------------------------------------
* 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.
[[Page 3208]]
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.
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 into the FAA-approved maintenance program the
maximum brake wear limits specified in paragraph TABLE 3 of this AD
for the applicable airplane model.
(2) Comply with those measurements thereafter.
(3) Measure the brake wear in accordance with Chapter 32-42-27
of the AMM; or Chapter 32-32-( ) of the brake manufacturer's CMM; or
the service bulletins (SB) listed in TABLE 4, below. Note that the
brake wear limits specified in TABLE 3 may be dependent on brake
stack weight. In those cases, refer to the service information
specified in TABLE 4 to verify that the correct brake stack weight
is being used.
(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 wear limit
Airplane model/Series Brake manufacturer Brake part No. (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 S.C.*........... BFGoodrich 2-1449 1.1'' (27.9 mm).
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-B4-200................. Messier-Bugatti C20060-100 Series 1.1'' (28.0 mm).
A300-600.................... Messier-Bugatti C20060-100 Series 1.1'' (28.0 mm).
A300-600.................... Messier-Bugatti C20175100 1.1'' (50.0 mm).
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).
A300 B4-600R................ Messier-Bugatti C20210500 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
[Service information sources containing measuring instructions that must be revised to accommodate the new brake
wear limits specified in TABLE 3. (Refer to paragraph (b)(3) of this AD.)]
----------------------------------------------------------------------------------------------------------------
Date/Revision (or
Brake manufacturer Part No. Document/Chapter later 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.............. CMM 32-44-37 January 30, 1993.
and S.C.*........... SB 567 (2-1449-32-4) January 30, 1993.
For Model A300 B4-100 Series
Airplanes:
[[Page 3209]]
Messier-Bugatti.............. A21329-41-17........ CMM 32-44-37 January 30, 1993.
ALS (Bendix)................. 2606802-3........... CMM 32-42-02 Revision 7/April
30, 1995.
2606802-4........... SB 2606802-32-003 March 31, 1993, and
Revision 1/October
1, 1993.
2606802-5 and S.C.*.
BFGoodrich................... 2-1449.............. CMM 32-44-37 January 30, 1993.
and S.C.*........... SB 567 (2-1449-32-4) 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
30, 1995.
2606802-4, 2606802-5 SB 2606802-32-003 March 31, 1993, and
and S.C.*. Revision 1/October
1, 1993.
For Model A300-600 Series
Airplanes:
Messier-Bugatti.............. C20060-100 Series... CMM 32-44-24 December 31, 1991.
Messier-Bugatti.............. C20175100........... CMM 32-44-50 November 30, 1991.
ALS (Bendix)................. 2607932-1 and S.C.*. CMM 32-42-05; Revision 4/February
15,1992.
SB 2607932-32-002; March 31,1993, and
Revision 1/October
1, 1993.
SB 2607932-32-003 May 31, 1995.
For Model A300 B4-600R Series
Airplanes:
Messier-Bugatti.............. C20210000........... CMM 32-44-51 August 31, 1994.
and C20210200 Series SB 470-32-675 Revision 1/
September 26,
1994.
Messier-Bugatti.............. C20210500 Series.... CMM 32-44-68 November 30, 1995.
For Model A310-200 Series
Airplanes:
Messier-Bugatti.............. C20089000 Series.... CMM 32-46-23 January 31, 1992.
ALS (Bendix)................. 2606822-1 and S.C... CMM 32-42-03 Revision 5/January
31, 1991.
SB 2606822-32-002 March 31, 1993.
For Model A310-300 Series
Airplanes:
Messier-Bugatti.............. C20194000........... CMM 32-46-37 August 31, 1994.
and 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........... CMM 32-47-20 January 31, 1995.
and C20225200 Series SB 580-32-3042 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.
(f) This amendment becomes effective on February 26, 1997.
Issued in Renton, Washington, on January 7, 1997.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 97-810 Filed 1-21-97; 8:45 am]
BILLING CODE 4910-13-U
