[Federal Register Volume 65, Number 37 (Thursday, February 24, 2000)]
[Proposed Rules]
[Pages 9225-9227]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-4336]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-28-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 an existing 
airworthiness directive (AD), applicable to all Airbus Model A319, 
A320, and A321 series airplanes, that currently requires repetitive 
inspections for discrepancies of the lock bolt for the pintle pin on 
the main landing gear (MLG), and follow-on corrective actions, if 
necessary. This action would require additional follow-on actions for 
certain airplanes. 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 
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.

DATES: Comments must be received by March 27, 2000.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 99-NM-28-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 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: 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:

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 99-NM-28-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

[[Page 9226]]

FAA, Transport Airplane Directorate, ANM-114, Attention: Rules Docket 
No. 99-NM-28-AD, 1601 Lind Avenue, SW., Renton, Washington 98055-4056.

Discussion

    On June 29, 1998, the FAA issued AD 98-14-11, amendment 39-10644 
(63 FR 36834, July 8, 1998), applicable to all Airbus Model A319, A320, 
and A321 series airplanes, to require repetitive inspections for 
discrepancies of the lock bolt for the pintle pin on the main landing 
gear (MLG), and follow-on corrective actions, if necessary. That action 
was prompted by two reports indicating that the forward pintle pin of 
the MLG had migrated forward toward the wing rear spar. In both 
instances, the lock bolt and associated MLG barrel bushings securing 
the pintle pin were missing, which allowed the pintle pin to migrate 
forward, although further movement was prevented by the incrementally 
tapered diameter of the pintle pin. Backward migration of the pintle 
pin also could occur, which would allow the pintle pin to become 
disengaged and separate from the pintle fitting bearing. 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.

Explanation of Relevant Service Information

    Since issuance of AD 98-14-11, Airbus issued Service Bulletin A320-
32-1187, dated June 17, 1998, and Revision 01, dated February 17, 1999. 
The original and revised service bulletin describe procedures for 
repetitive detailed visual inspections for discrepancies (rotation, 
wear, and missing or broken parts) of the lock bolt for the MLG pintle 
pin, and follow-on corrective actions, if necessary. The corrective 
actions include replacement of a discrepant lock bolt with a new or 
serviceable part, and relubrication of the pintle fitting bearing. The 
inspection procedure of the service bulletin is different from that 
described in Airbus All Operator Telex (AOT) 32-17, Revision 01, dated 
November 6, 1997 (which was cited in AD 98-14-11 as the appropriate 
source of service information). The service bulletin includes 
procedures for additional follow-on and corrective actions, including a 
one-time retorque of the lock bolt for the pintle pin if there is no 
sign that the lock bolt has turned, and replacement of the lock bolt 
with a new lock bolt. In addition, Revision 01 of the service bulletin 
includes procedures for additional follow-on actions, including 
application of sealant to the head of the lockbolt. The Direction 
Generale de l'Aviation Civile (DGAC), which is the airworthiness 
authority for France, approved the original service bulletin and 
classified Revision 01 as mandatory, and issued French airworthiness 
directive 97-385-112(B)R1, dated October 21, 1998, in order to ensure 
the 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 98-14-11 to 
continue to require repetitive inspections for discrepancies of the 
lock bolt for the pintle pin on the main landing gear (MLG), and 
follow-on corrective actions, if necessary; and would require 
additional follow-on actions, including a retorque of the lock bolt for 
the pintle pin. In addition, the FAA has added a note to clarify the 
definition of a detailed visual inspection.

Interim Action

    This is considered to be interim action until final action is 
identified, at which time the FAA may consider further rulemaking.

Cost Impact

    The FAA estimates that 341 airplanes of U.S. registry would be 
affected by this proposed AD. It would take approximately 2 work hours 
per airplane to accomplish the proposed inspection, at an average labor 
rate of $60 per work hour. Based on these figures, the cost impact of 
the inspection proposed by this AD on U.S. operators is estimated to be 
$40,920, or $120 per airplane, per inspection cycle.
    The cost impact figure discussed above is based on assumptions that 
no operator has yet accomplished any of the 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 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 amendment 39-10644 (63 FR 
36834, July 8, 1998), and by adding a new airworthiness directive (AD), 
to read as follows:

Airbus Industrie: Docket 99 -NM-28-AD. Supersedes AD 98-14-11, 
Amendment 39-10644.

    Applicability: All Model A319, A320, and A321 series airplanes; 
certificated in any category.


[[Page 9227]]


    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 (c) 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 a rotated, damaged, or missing lock bolt, 
which could result in disengagement of the pintle pin from the 
bearing, and consequent collapse of the main landing gear (MLG) 
during landing, accomplish the following:

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. 
After the effective date of this AD, 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 Industrie 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 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.''

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.

Alternative Methods of Compliance

    (c) 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 request 
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

    (d) 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 4: The subject of this AD is addressed in French 
airworthiness directive 97-385-112(B)R1, dated October 21, 1998.


    Issued in Renton, Washington, on February 17, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-4336 Filed 2-23-00; 8:45 am]
BILLING CODE 4910-13-P