[Federal Register Volume 66, Number 226 (Friday, November 23, 2001)]
[Proposed Rules]
[Pages 58684-58687]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-29193]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-338-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A319, A320, and A321 
Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the supersedure of two existing 
airworthiness directives (AD), applicable to certain Airbus Model A319, 
A320, and A321 series airplanes. The first AD currently requires 
removing the existing forward pintle nut and cross bolt on the main 
landing gear (MLG), and installing a new nylon spacer and cross bolt 
and nut. The second AD currently requires repetitive inspections for 
discrepancies of the lock bolt for the pintle pin on the MLG, follow-on 
corrective actions if necessary, and retorquing of the forward pintle 
pin lock bolt for certain airplanes. That AD also provides for an 
optional terminating action. This action would cancel the requirements 
of the first AD, continue the requirements of the second AD, and 
require the previously optional terminating action that was provided 
for in the second AD. This proposal is prompted by issuance of 
mandatory continuing airworthiness information by a foreign civil 
airworthiness authority. The actions specified by the proposed AD are 
intended to prevent a rotated, damaged, or missing lock bolt, which 
could result in disengagement of the pintle pin from the pintle fitting 
bearing, and consequent collapse of the MLG during landing.

DATES: Comments must be received by December 24, 2001.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2000-NM-338-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9 a.m. and 3 p.m., Monday through Friday, except 
Federal holidays. 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 fax or the Internet must 
contain ``Docket No. 2000-NM-338-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 the proposed rule may be 
obtained from Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 
Blagnac Cedex, France. This information may be examined at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington.

FOR FURTHER INFORMATION CONTACT: Tim Dulin, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2141; fax (425) 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 action may be changed in 
light of the comments received.

[[Page 58685]]

    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 proposed 
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 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 action must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2000-NM-338-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-114, Attention: Rules 
Docket No. 2000-NM-338-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    On May 9, 1996, the FAA issued AD 96-10-18, amendment 39-9625 (61 
FR 24690, May 16, 1996), applicable to certain Airbus Model A320-111, -
211, -212, and -231 series airplanes, to require removing the existing 
forward pintle nut and cross bolt on the main landing gear (MLG) and 
installing a new nylon spacer and cross bolt and nut. That action was 
prompted by results of fatigue testing which revealed that the cross 
bolt and nut in the forward pintle pin of the MLG were damaged due to 
fatigue cracking. The requirements of that AD are intended to prevent 
such fatigue cracking, which could result in collapse of the MLG.
    On May 16, 2000, the FAA issued AD 2000-10-16, amendment 39-11740 
(65 FR 34059, May 26, 2000), to require repetitive inspections for 
discrepancies of the lock bolt for the pintle pin on the MLG; follow-on 
corrective actions, if necessary; and retorquing of the forward pintle 
pin lock bolt for certain airplanes. That AD also provides for an 
optional terminating action for the requirements of the AD. That action 
was prompted by issuance of mandatory continuing airworthiness 
information by a foreign civil airworthiness authority. The 
requirements of that AD are intended to detect and correct a rotated, 
damaged, or missing lock bolt, which could result in disengagement of 
the pintle pin from the pintle fitting bearing, and consequent collapse 
of the MLG during landing. In the ``Comment Received'' section of that 
AD, the FAA stated that it may consider further rulemaking if a 
determination is made at a later date that the terminating modification 
should be mandated.

Actions Since Issuance of Previous Rules

    Since the issuance of AD 96-10-18 and AD 2000-10-16, the Direction 
Generale de l'Aviation Civile (DGAC), which is the airworthiness 
authority for France, has issued French airworthiness directive 2000-
428-153(B), Revision 1, dated November 29, 2000, to continue to require 
the repetitive inspections of the lock bolt for the pintle pin on the 
MLG and follow-on corrective actions, and to mandate the optional 
terminating action modification identified in AD 2000-10-16.

Explanation of Relevant Service Information

    Airbus has issued Service Bulletin A320-32-1213, Revision 02, dated 
February 9, 2001, which describes procedures for modification of the 
pintle pin attachment of both the left and right MLG to incorporate a 
dual lock bolt configuration. Modification includes a detailed visual 
inspection of the pintle pin lock bolts to ensure that the bolts are in 
proper position and are not broken, and repair if necessary; and 
removal and installation of the lock bolts. Accomplishment of the 
actions specified in the service bulletin is intended to adequately 
address the identified unsafe condition. The DGAC classified this 
service bulletin as mandatory and issued French airworthiness directive 
2000-428-153(B), Revision 1, dated November 29, 2000, in order to 
assure the continued airworthiness of these airplanes in France.

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. Pursuant to this 
bilateral airworthiness agreement, the DGAC has kept the FAA informed 
of the situation described above. The FAA has examined the findings of 
the DGAC, reviewed all available information, and determined that AD 
action is necessary for products of this type design that are 
certificated for operation in the United States.

Explanation of Requirements of Proposed 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, the proposed AD would supersede AD 2000-10-16, to 
continue to require repetitive inspections of the lock bolt for the 
pintle pin on the MLG, follow-on corrective actions if necessary, and 
retorquing of the forward pintle pin lock bolt for certain airplanes. 
This proposed AD also would add a requirement for accomplishment of the 
terminating action modification in accordance with the service bulletin 
described previously, which would constitute terminating action for the 
repetitive inspection requirements of the AD. In addition, the proposed 
AD would supersede AD 96-10-18, to cancel the requirements of that AD.

Differences Between Proposed Rule and Foreign Airworthiness 
Directive

    The proposed AD would differ from the parallel French airworthiness 
directive in that it would not require accomplishment of Airbus Service 
Bulletin A320-32-1119, followed by repetitive inspections, as an 
interim action alternative to Airbus Service Bulletin A320-32-1213, 
unless it is specifically required to correct a discrepancy found 
during inspection.

Cost Impact

    There are approximately 341 airplanes of U.S. registry that would 
be affected by this proposed AD.
    The actions that are currently required by AD 2000-10-16 take 
approximately 2 work hours per airplane to accomplish, at an average 
labor rate of $60 per work hour. Based on these figures, the cost 
impact of the currently required actions on U.S. operators is estimated 
to be $120 per airplane, per inspection cycle.
    The new action that is proposed in this AD action would take 
approximately 3 work hours per airplane to accomplish, at an average 
labor rate of $60 per work hour. Required parts would cost 
approximately $540 per airplane. Based on these figures, the cost 
impact of the proposed new requirements of this AD

[[Page 58686]]

on U.S. operators is estimated to be $245,520, or $720 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. The cost 
impact figures discussed in AD rulemaking actions represent only the 
time necessary to perform the specific actions actually required by the 
AD. These figures typically do not include incidental costs, such as 
the time required to gain access and close up, planning time, or time 
necessitated by other administrative actions.

Regulatory Impact

    The regulations proposed herein would 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 proposal would not have federalism implications 
under Executive Order 13132.
    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 amendments 39-11740 (65 FR 
34059, May 26, 2000), and 39-9625 (61 FR 24690, May 16, 1996) and by 
adding a new airworthiness directive (AD), to read as follows:

Airbus Industrie: Docket 2000-NM-338-AD. Supersedes AD 2000-10-16, 
Amendment 39-11740, and AD 96-10-18, Amendment 39-9625.

    Applicability: Model A319, A320, and A321 series airplanes, 
certificated in any category, except those on which Airbus Service 
Bulletin A320-32-1213, dated March 21, 2000 (reference Airbus 
Modification 28903 or 30044) has been accomplished.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
otherwise 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)(1) 
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 a rotated, damaged, or missing lock bolt, which could 
result in disengagement of the pintle pin from the pintle fitting 
bearing, and consequent collapse of the main landing gear (MLG) 
during landing, accomplish the following:

    Note 2: Paragraphs (a) and (b) of this AD repeat the actions 
that were previously mandated by AD 2000-10-16. The intent of 
including these paragraphs is to ensure that the currently-required 
repetitive inspections continue to be accomplished until the 
terminating modifications are installed.

Restatement of Requirements of AD 2000-10-16

Inspection

    (a) Perform a detailed visual inspection to detect discrepancies 
(rotation, damage, and absence) of the lock bolt for the pintle pin 
on the MLG, in accordance with Airbus All Operator Telex (AOT) 32-
17, Revision 01, dated November 6, 1997; Airbus Service Bulletin 
A320-32-1187, dated June 17, 1998; or Airbus Service Bulletin A320-
32-1187, Revision 01, dated February 17, 1999; at the latest of the 
times specified in paragraphs (a)(1), (a)(2), and (a)(3) of this AD. 
If any discrepancy is detected, prior to further flight, perform 
corrective actions, as applicable, in accordance with the AOT or 
service bulletin. Repeat the inspection thereafter at intervals not 
to exceed 1,000 flight cycles or 15 months, whichever occurs first, 
unless the terminating action of paragraph (c) of this AD is 
accomplished. After June 30, 2000 (the effective date of AD 2000-10-
16, amendment 39-11740), only Airbus Service Bulletin A320-32-1187, 
Revision 01, dated February 17, 1999, shall be used for compliance 
with this paragraph.
    (1) Within 30 months since the airplane's date of manufacture or 
prior to the accumulation of 2,000 total flight cycles, whichever 
occurs first.
    (2) Within 15 months or 1,000 flight cycles after the last gear 
replacement or accomplishment of Airbus Service Bulletin A320-32-
1119, dated June 13, 1994, whichever occurs first.
    (3) Within 500 flight cycles after August 12, 1998 (the 
effective date of AD 98-14-11, amendment 39-10644).

    Note 3: 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.''

One-time Follow-on Actions

    (b) For airplanes on which the actions described in paragraph 
2.B.(2)(c) of Airbus Service Bulletin A320-32-1187, Revision 01, 
dated February 17, 1999, have not been accomplished: At the time of 
the initial inspection or the next repetitive inspection required by 
paragraph (a) of this AD, perform the applicable one-time follow-on 
actions (including retorquing the forward pintle pin lock bolt and 
applying sealant to the head of the lock bolt), in accordance with 
section 2.B.(2)(c) of the Accomplishment Instructions of Airbus 
Service Bulletin A320-32-1187, Revision 01, dated February 17, 1999.

New Actions Required by This AD

Terminating Modification

    (c) Within 5 years from the effective date of this AD, or at the 
next MLG overhaul, whichever occurs later, modify the forward pintle 
pin cross bolt on both the left and right MLG (including a detailed 
visual inspection to ensure that the bolts are in proper position 
and are not broken, and repair if necessary; and removal and 
installation of the lock bolts), in accordance with Airbus Service 
Bulletin A320-32-1213, Revision 02, dated February 9, 2001. This 
modification constitutes terminating action for the requirements of 
this AD.

    Note 4: Accomplishment of the actions required in paragraph (c) 
of this AD, prior to the effective date of this AD, in accordance 
with Airbus Service Bulletin A320-32-1213, dated March 21, 2000, or 
Revision 01, dated November 15, 2000, is considered acceptable for 
compliance with paragraph (c) of this AD.

Alternative Methods of Compliance

    (d)(1) 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, 
Transport Airplane Directorate, FAA. Operators shall

[[Page 58687]]

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.
    (2) Alternative methods of compliance, approved previously in 
accordance with AD 2000-10-16, amendment 39-11740, are approved as 
alternative methods of compliance with this AD.

    Note 5: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Manager, International Branch, ANM-116.

Special Flight Permits

    (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.

    Note 6: The subject of this AD is addressed in French 
airworthiness directive 2000-428-153(B), Revision 1, dated November 
29, 2000.


    Issued in Renton, Washington, on November 15, 2001.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-29193 Filed 11-21-01; 8:45 am]
BILLING CODE 4910-13-U