[Federal Register Volume 65, Number 141 (Friday, July 21, 2000)]
[Rules and Regulations]
[Pages 45277-45280]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-18281]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-210-AD; Amendment 39-11824; AD 2000-14-14]
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 
repetitive inspections to determine the length of the wear indicator 
pins of the main brake assemblies of the main landing gear (MLG); 
follow-on inspections; and corrective actions, if necessary. This 
amendment is prompted by reports from several operators that severe 
oxidation was found on the rotor disk assemblies of the main brake 
assemblies. This action is necessary to detect and correct thermal 
oxidation of the main brake assemblies, which could result in 
deterioration of the MLG brakes, and consequent reduced braking 
performance.

DATES: Effective August 7, 2000.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of August 7, 2000.
    Comments for inclusion in the Rules Docket must be received on or 
before August 21, 2000.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2000-NM-210-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. Comments may be submitted via fax to (425) 227-1232. 
Comments may also be sent via the Internet using the following address: 
[email protected]. Comments sent via the Internet must contain 
``Docket No. 2000-NM-210-AD'' in the subject line and need not be 
submitted in triplicate. Comments sent via the Internet as attached 
electronic files must be formatted in Microsoft Word 97 for Windows or 
ASCII text.
    The service information referenced in this AD may be obtained from 
BFGoodrich Aerospace Wheel & Brake Systems Division, 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: On November 24, 1999, the FAA issued AD 99-
25-07, amendment 39-11450 (64 FR 68620, December 8, 1999), which is 
applicable to certain BFGoodrich main brake assemblies having part 
number (P/N) 2-1598 or P/N 2-1600 as installed on Airbus Model A319 and 
A320 series airplanes. That AD 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. That AD also requires modification of the main brake 
assemblies of the MLG to shorten the wear indicator pins, and change P/
N 2-1598 to P/N 2-1598-1 or change P/N 2-1600 to P/N 2-1600-1. In 
addition, that AD requires incorporation of specified wear limits into 
the maintenance inspection program.
    Since the issuance of AD 99-25-07, the FAA has received reports 
from several operators of severe oxidation on the carbon heat sinks 
used on BFGoodrich main brake assemblies, P/N 2-1598-1 and P/N 2-1600-
1, installed on Airbus Model A319 and A320 series airplanes. Those 
reports indicate that the accomplishment of AD 99-25-07 did not 
adequately address the problem of oxidation on the main brake 
assemblies in time to correct the identified unsafe condition. 
Investigation has revealed that deterioration of the BFGoodrich main 
brake assemblies was caused by thermal oxidation of the carbon material 
on the heat sinks used in the main brake assemblies, P/N 2-1598-1 and 
P/N 2-1600-1, 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 the carbon brakes, which are 
susceptible to this oxidation condition, are used only on Airbus Model 
A319 and A320 series airplanes. Such oxidation first develops on the 
inner diameter of the rotor disk assemblies when the brake assembly is 
almost worn-to-limit. 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 2-1598-32-2 and 2-1600-32-
3, both dated June 16, 2000, which describe procedures for an initial 
inspection to determine the length of the wear indicator pins of the 
MLG main brake assemblies and repetitive inspections thereafter at 
certain intervals. Procedures include follow-on inspections if the 
length of either wear indicator pin measures between 0.60 and 0.70 
inches, or if the length of the pin measures between 0.20 and 0.30 
inches; and corrective actions, if necessary. Follow-on inspections

[[Page 45278]]

include inspecting the rotor disks located in the center of the heat 
sinks of the main brake assemblies of the MLG to detect the level of 
oxidation on the brake assemblies. Corrective actions include 
replacement of the main brake assembly with a new assembly if any 
oxidation exceeding the limits specified in the applicable service 
bulletin is detected. Following such replacement, repetitive 
inspections of the wear indicator pins are continued.

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 detect and correct 
thermal oxidation of the main brake assemblies, which could result in 
deterioration of the MLG brakes, and consequent reduced braking 
performance. This AD requires repetitive inspections to determine the 
length of the wear indicator pins of each main brake assembly of the 
MLG; follow-on inspections; and corrective actions, if necessary. The 
actions are required to be accomplished in accordance with the 
applicable service bulletin described previously, except as discussed 
below.

Differences Between AD and Service Information

    Operators should note that the previously referenced BFGoodrich 
service bulletins recommend accomplishment of an initial inspection on 
all MLG brake assemblies to determine the length of the wear indicator 
pins ``as soon as possible.'' However, the FAA finds that a definitive 
compliance time is necessary. Therefore, paragraph (a) of this AD 
requires the accomplishment of the repetitive inspections within 10 
days after the effective date of this AD, or within 500 flight cycles 
after replacement of any brake assembly, whichever occurs later. The 
FAA considers that such a compliance time represents an appropriate 
interval of time allowable for affected airplanes to continue to 
operate without compromising safety.
    Operators should note that the previously referenced service 
bulletins include procedures for a one-time inspection on all brakes 
when any wear indicator pin measures between 0.60 to 0.70 inches, and 
another such inspection when any pin measures between 0.20 to 0.30 
inches. However, the FAA has determined that it is necessary to change 
those wear indicator pin measurements in this AD to ensure that all 
brakes are inspected at appropriate intervals. Paragraph (b) of this AD 
requires a one-time inspection of the brake if either wear indicator 
pin measures between 0.31 and 0.70 inches, and paragraph (c) of this AD 
requires an inspection of the brake if either wear indicator pin 
measures 0.30 inches or less. In the event that the special detailed 
inspection required by paragraph (c) of this AD is accomplished prior 
to paragraph (b) of this AD, the inspection required by paragraph (b) 
of this AD is deemed unnecessary.

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.

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.
    Submit comments using the following format:
     Organize comments issue-by-issue. For example, discuss a 
request to change the compliance time and a request to change the 
service bulletin reference as two separate issues.
     For each issue, state what specific change to the AD is 
being requested.
     Include justification (e.g., reasons or data) for each 
request.
    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 2000-NM-210-AD.'' The postcard will be date stamped 
and returned to the commenter.

Regulatory Impact

    The regulations adopted herein will not have a substantial direct 
effect 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, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    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.

[[Page 45279]]

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:

2000-14-14  BFGoodrich: Amendment 39-11824. Docket 2000-NM-210-AD.

    Applicability: Model BFGoodrich main brake assemblies having 
part number (P/N) 2-1598-1 or P/N 2-1600-1, 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 (e) 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 detect and correct thermal oxidation of the main brake 
assemblies, which could result in deterioration of the main landing 
gear (MLG) brakes, and consequent reduced braking performance, 
accomplish the following:

Initial and Repetitive Inspections

    (a) Within 10 days after the effective date of this AD, or 
within 500 flight cycles after replacement of any brake assembly, 
whichever occurs later: Perform an inspection to determine the 
length of the wear indicator pins of each main brake assembly of the 
MLG, in accordance with the Accomplishment Instructions of 
BFGoodrich Service Bulletin 2-1598-32-2 or 2-1600-32-3, both dated 
June 16, 2000, as applicable. Repeat the inspection thereafter for 
each brake assembly as specified by paragraph (a)(1), (a)(2), 
(a)(3), or (a)(4), as applicable.
    (1) If the length of both wear indicator pins is greater than 
2.00 inches, repeat the inspection thereafter at intervals not to 
exceed 500 flight cycles.
    (2) If the length of the shortest wear indicator pin is between 
2.00 and 1.50 inches, repeat the inspection thereafter at intervals 
not to exceed 250 flight cycles.
    (3) If the length of the shortest wear indicator pin is between 
1.49 and 1.0 inches, repeat the inspection thereafter at intervals 
not to exceed 100 flight cycles.
    (4) If the length of the shortest wear indicator pin is between 
0.31 and 0.99 inches, repeat the inspection thereafter at intervals 
not to exceed 10 days.
    (5) If the length of the shortest wear indicator pin is less 
than 0.31 inches, no further action is required by this paragraph 
until the brake is replaced.

Follow-on Inspections and Corrective Actions

    (b) During any inspection required by paragraph (a) of this AD, 
if the length of the shortest wear indicator pin measures between 
0.31 and 0.70 inches: Prior to further flight, perform a one-time 
special detailed inspection of the rotor disks located in the center 
of the heat sinks of the main brake assemblies of the MLG to detect 
the level of oxidation on the main brake assemblies in accordance 
with the Accomplishment Instructions of BFGoodrich Service Bulletin 
2-1598-32-2 or 2-1600-32-3, both dated June 16, 2000, as applicable. 
The inspection required by this paragraph is required only the first 
time the length of the shortest wear indicator pin measures between 
0.31 and 0.70 inches.
    (1) If no oxidation is detected, or if oxidation within the 
limits specified in the applicable service bulletin is detected on 
any brake assembly, continue the inspections required by paragraph 
(a) of this AD.
    (2) If any oxidation exceeding the limits specified in the 
applicable service bulletin is detected on any brake assembly, prior 
to further flight, replace the brake assembly with a new brake 
assembly in accordance with the applicable service bulletin. Within 
500 flight cycles following such replacement, continue the 
inspections required by paragraph (a) of this AD.

    Note 2: For the purposes of this AD, a special detailed 
inspection is defined as: ``An intensive examination of a specific 
item(s), installation, or assembly to detect damage, failure, or 
irregularity. The examination is likely to make extensive use of 
specialized inspection techniques and/or equipment. Intricate 
cleaning and substantial access or disassembly procedures may be 
required.''

    (c) During any inspection required by paragraph (a) of this AD, 
if the length of the shortest wear indicator pin measures 0.30 
inches or less: Prior to further flight, perform a one-time special 
detailed inspection of the rotor disks located in the center of the 
heat sinks of the main brake assemblies of the MLG to detect the 
level of oxidation on the main brake assemblies in accordance with 
the Accomplishment Instructions of BFGoodrich Service Bulletin 2-
1598-32-2 or 2-1600-32-3, both dated June 16, 2000, as applicable. 
The inspection required by this paragraph is required only the first 
time the length of the shortest wear indicator pin measures 0.30 
inches or less.
    (1) If no oxidation is detected, or if oxidation within the 
limits specified in the applicable service bulletin is detected on 
any brake assembly, no further action is required by this AD until 
the brake is replaced in accordance with the FAA-approved 
maintenance program. Within 500 flight cycles following such 
replacement, continue the inspections required by paragraph (a) of 
this AD.
    (2) If any oxidation exceeding the limits specified in the 
applicable service bulletin is detected on any brake assembly, prior 
to further flight, replace the brake assembly with a new brake 
assembly in accordance with the applicable service bulletin. Within 
500 flight cycles following such replacement, continue the 
inspections required by paragraph (a) of this AD.

Spares

    (d) As of the effective date of this AD, no person shall install 
on any airplane a BFGoodrich main brake assembly having P/N 2-1598-1 
or P/N 2-1600-1 if the wear indicator pin measures 0.70 inches or 
less, unless an inspection to detect oxidation of the brake assembly 
has been accomplished in accordance with paragraph 3.A.(3) of the 
Accomplishment Instructions of BFGoodrich Service Bulletin 2-1598-
32-2 or 2-1600-32-3, both dated June 16, 2000, as applicable.

Alternative Methods of Compliance

    (e) 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 3: 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

    (f) 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.

Incorporation by Reference

    (g) Except as provided by paragraph (c)(1) of this AD, the 
inspections and replacement actions shall be done in accordance with 
BFGoodrich Service Bulletin 2-1598-32-2, dated June 16, 2000, or 
BFGoodrich Service Bulletin 2-1600-32-3, dated June 16, 2000; 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 Aerospace 
Wheel & Brake Systems Division, P.O. Box 340, Troy, Ohio, 45373. 
Copies may be inspected at the FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington; or at the Office of the 
Federal

[[Page 45280]]

Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

Effective Date

    (h) This amendment becomes effective on August 7, 2000.

    Issued in Renton, Washington, on July 13, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-18281 Filed 7-20-00; 8:45 am]
BILLING CODE 4910-13-U