[Federal Register Volume 64, Number 235 (Wednesday, December 8, 1999)]
[Rules and Regulations]
[Pages 68620-68623]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-31474]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 99-NM-341-AD; Amendment 39-11450; AD 99-25-07]
RIN 2120-AA64
Airworthiness Directives; BFGoodrich Main Brake Assemblies as
Installed on Airbus Model A319 and A320 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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SUMMARY: This amendment adopts a new airworthiness directive (AD) that
is applicable to certain BFGoodrich main brake assemblies as installed
on Airbus Model A319 and A320 series airplanes. This action requires a
one-time inspection of the wear indicator pins to determine the level
of wear of the main brake assemblies of the main landing gear (MLG),
and corrective actions, if necessary. This action also requires
modification of the main brake assemblies of the MLG, and incorporation
of specified wear limits into the maintenance inspection program. This
amendment is prompted by in-service reports of brake deterioration
caused by thermal
[[Page 68621]]
oxidation of the carbon disks of certain BFGoodrich main brake
assemblies. The actions specified in this AD are intended to prevent
thermal oxidation of the main brake assemblies, which could result in
deterioration of the MLG brakes, and consequent reduced braking
performance.
DATES: Effective December 23, 1999.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of December 23, 1999.
Comments for inclusion in the Rules Docket must be received on or
before January 7, 2000.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 99-NM-341-AD, 1601 Lind Avenue, SW.,
Renton, Washington 98055-4056.
The service information referenced in this AD may be obtained from
BFGoodrich Aircraft Wheels and Brakes, P.O. Box 340, Troy, Ohio, 45373.
This information may be examined at the FAA, Transport Airplane
Directorate, 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: Norman B. Martenson, Manager,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2110; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION: The FAA has received in-service reports of
brake deterioration of certain BFGoodrich main brake assemblies
installed on Airbus Model A319 and A320 series airplanes. Investigation
revealed that the deterioration of these BFGoodrich brakes was caused
by thermal oxidation of the carbon material due to exposure to elevated
temperatures for prolonged periods of time. Further investigation
revealed that the oxidation inhibitor process used by BFGoodrich does
not completely prevent oxidation of the carbon brake material.
BFGoodrich advises that these carbon brakes, which are susceptible to
this oxidation condition, are only used on Airbus Model A319 and A320
series airplanes. This condition, if not corrected, could result in
deterioration of the MLG brakes, and consequent reduced braking
performance.
Explanation of Relevant Service Information
BFGoodrich has issued Service Bulletins 2-1598-32-1, and 2-1600-32-
2, both dated November 5, 1999, which describe procedures for removal
of main brake assemblies with wear indicator pins having a length of
0.20 inch or less, and modification of the main brake assemblies of the
MLG. The modification involves reducing the length of the wear
indicator pins, and re-identifying the piston housings and
identification plates of the main brake assemblies.
FAA's Determination
The FAA has determined that a direct correlation exists between the
amount of wear and the degree of thermal oxidation. Therefore, by
limiting the wear of the carbon brake assemblies, as required by this
AD, thermal oxidation is controlled to an acceptable level.
FAA's Conclusions
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 Rule
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, this AD is being issued to prevent thermal
oxidation of the main brake assemblies, which could result in
deterioration of the MLG brakes, and consequent reduced braking
performance. This AD requires one-time detailed visual inspection of
the wear indicator pins to determine the level of wear of the main
brake assemblies of the main landing gear (MLG), and corrective
actions, if necessary. This AD also requires modification of the main
brake assemblies of the MLG, and incorporation of specified wear limits
into the FAA-approved maintenance inspection program. Certain actions
are required to be accomplished in accordance with the service
bulletins described previously, except as discussed below.
Interim Action
This is considered to be interim action. The brake manufacturer has
advised that it currently is developing a modification that will
positively address the unsafe condition addressed by this AD. Once this
modification is developed, approved, and available, the FAA may
consider additional rulemaking.
Differences Between AD and Service Information
Operators should note that the BFGoodrich service bulletins allow
an option of either replacement of any main brake assembly with 0.20
inch or less remaining on the wear indicator pins, or modification of
the brake assembly by reducing the wear indicator pins. Additionally,
the BFGoodrich service bulletins do not recommend a compliance time for
either action. However, this AD requires a one-time inspection of the
wear indicator pins within 10 days, and replacement of the brake
assembly if the remaining length of the wear indicator pin is equal to
or less than 0.20 inch. This AD also requires modification of the brake
assembly to reduce the length of the wear indicator pins within 30
days, and re-identification of the piston housings and identification
plates no later than the next brake removal. The FAA finds that in view
of in-service reports of main brake assembly deterioration, the
requirements specified in this AD are appropriate to maintain a
consistent main brake assembly configuration for all airplanes that are
affected by the subject unsafe condition.
Determination of Rule's Effective Date
Since a situation exists that requires the immediate adoption of
this regulation, it is found that notice and opportunity for prior
public comment hereon are impracticable, and that good cause exists for
making this amendment effective in less than 30 days.
Comments Invited
Although this action is in the form of a final rule that involves
requirements affecting flight safety and, thus, was not preceded by
notice and an opportunity for public comment, comments are invited on
this rule. Interested persons are invited to comment on this 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 under the caption ADDRESSES. All
communications received on or before the closing date for comments will
be considered, and this rule may be amended in light of the comments
received. Factual information that supports the commenter's ideas and
suggestions is extremely helpful in evaluating the effectiveness of the
AD action and determining whether additional rulemaking action would be
needed.
[[Page 68622]]
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the rule that might
suggest a need to modify the 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 that
summarizes each FAA-public contact concerned with the substance of this
AD will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this rule must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 99-NM-341-AD.'' The postcard will be date stamped and
returned to the commenter.
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.
The FAA has determined that this regulation is an emergency
regulation that must be issued immediately to correct an unsafe
condition in aircraft, and that it is not a ``significant regulatory
action'' under Executive Order 12866. It has been determined further
that this action involves an emergency regulation under DOT Regulatory
Policies and Procedures (44 FR 11034, February 26, 1979). If it is
determined that this emergency regulation otherwise would be
significant under DOT Regulatory Policies and Procedures, a final
regulatory evaluation will be prepared and placed in the Rules Docket.
A copy of it, if filed, 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, Incorporation by
reference, 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 adding the following new
airworthiness directive:
99-25-07 BFGoodrich: Amendment 39-11450. Docket 99-NM-341-AD.
Applicability: BFGoodrich main brake assemblies having part
number (P/N) 2-1598 or 2-1600, as installed on Airbus Model A319 and
A320 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 (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 thermal oxidation of the main brake assemblies of the
main landing gear (MLG), which could result in deterioration of the
MLG brakes, and consequent reduced braking performance, accomplish
the following:
Detailed Visual Inspection
(a) Within 10 days after the effective date of this AD, perform
a one-time detailed visual inspection of the wear indicator pins to
determine the level of wear of the main brake assemblies of the MLG,
as specified in BFGoodrich Service Bulletin 2-1598-32-1, or 2-1600-
32-2, both dated November 5, 1999, as applicable.
Note 2: For the purposes of this AD, a detailed visual
inspection is defined as: ``An intensive visual examination of a
specific structural area, system, installation, or assembly to
detect damage, failure, or irregularity. Available lighting is
normally supplemented with a direct source of good lighting at
intensity deemed appropriate by the inspector. Inspection aids such
as mirror, magnifying lenses, etc. may be used. Surface cleaning and
elaborate access procedures may be required.''
(1) If the remaining length of any wear indicator pin is less
than or equal to 0.20 inch (5.1 mm) with the brake pressurized,
prior to further flight, replace the brake assembly with a new or
serviceable brake assembly, in accordance with Chapter 32-42-27 of
the applicable Airplane Maintenance Manual (AMM).
(2) If the remaining length of all wear indicator pins is
greater than 0.20 inch (5.1 mm) with the brake pressurized, no
further action is required by this paragraph.
Modification
(b) Within 30 days after the effective date of this AD, modify
the main brake assemblies of the MLG by reducing the length of the
wear indicator pins, in accordance with BFGoodrich Service Bulletin
2-1598-32-1, or 2-1600-32-2, both dated November 5, 1999, as
applicable; and incorporate the new wear limits for the main brake
assemblies specified in the applicable service bulletin into the
FAA-approved maintenance program and comply with those limits
thereafter. After accomplishing the modification, but no later than
the next brake removal, re-identify the brake assemblies in
accordance with the applicable service bulletin.
Note 3: Once an operator has complied with the requirements of
paragraph (b) of this AD, that paragraph does not require that
operators subsequently record accomplishment of the requirements
each time a brake is inspected or overhauled in accordance with that
operator's FAA-approved maintenance inspection program.
Spares
(c) As of the effective date of this AD, no person shall install
on any airplane a BFGoodrich main brake assembly having P/N 2-1598
or 2-1600, unless that assembly has been modified in accordance with
this AD.
Alternative Methods of Compliance
(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, International Branch, ANM-116, 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, International
Branch, ANM-116.
Note 4: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the International Branch, ANM-116.
Special Flight Permits
(e) Special flight permits may be issued in accordance with
Secs. 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.
Incorporation by Reference
(f) The actions shall be done in accordance with BFGoodrich
Service Bulletin 2-1598-32-1, dated November 5, 1999, or BFGoodrich
Service Bulletin 2-1600-32-2, dated November 5, 1999, as applicable.
This incorporation by reference was approved by the Director of the
Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part
51. Copies may be obtained from BFGoodrich Aircraft Wheels and
Brakes, P.O. Box 340, Troy, Ohio, 45373. Copies may be
[[Page 68623]]
inspected at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington; or at the Office of the Federal
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.
(g) This amendment becomes effective on December 23, 1999.
Issued in Renton, Washington, on November 24, 1999.
D.L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 99-31474 Filed 12-7-99; 8:45 am]
BILLING CODE 4910-13-U
