AD 2000-10-16

[Federal Register Volume 65, Number 103 (Friday, May 26, 2000)]
[Rules and Regulations]
[Pages 34059-34061]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 00-12815]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-28-AD; Amendment 39-11740; AD 2000-10-16]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A319, A320, and A321 
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 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 
amendment requires additional follow-on actions for certain airplanes. 
This amendment also provides for optional terminating action for the 
requirements of this AD. This amendment is prompted by issuance of 
mandatory continuing airworthiness information by a foreign civil 
airworthiness authority. The actions specified by this 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: Effective June 30, 2000.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of June 30, 2000.
    The incorporation by reference of certain other publications, as 
listed in the regulations, was approved previously by the Director of 
the Federal Register as of August 12, 1998 (63 FR 36834, July 8, 1998).

ADDRESSES: The service information referenced in this AD may be 
obtained from Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 
Blagnac Cedex, France. 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: 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: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 98-14-11, 
amendment 39-10644 (63 FR 36834, July 8, 1998), which is applicable to 
all Airbus Model A319, A320, and A321 series airplanes, was published 
in the Federal Register on February 24, 2000 (65 FR 9225). The action 
proposed 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 to 
require additional follow-on actions, including a retorque of the lock 
bolt for the pintle pin.

Comment Received

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comment received.

Reference to Terminating Modification

    Two commenters request that the proposed AD include reference to 
Airbus Modifications 28903 (for Model A319 and A320 series airplanes) 
and 30044 (for Model A321 series airplanes) as terminating action to 
the requirements of this AD. Airbus Service Bulletin A320-32-1213, 
dated March 21, 2000, describes procedures for accomplishment of the 
modification, which involves installation of a dual lock bolt 
configuration. One commenter notes that the Direction Generale de 
l'Aviation Civile (DGAC), which is the airworthiness authority of 
France, has approved this modification as terminating action for the 
inspections and actions described in Airbus Service Bulletin A320-32-
1187.
    The FAA concurs that the modification described in Airbus Service 
Bulletin A320-32-1213 constitutes acceptable terminating action to the 
requirements of this AD. A new paragraph (c) has been added to the AD 
to provide this option to operators, and the applicability of the AD 
has been limited to those airplanes not having the modification. 
Additionally, since terminating action is now available, the FAA has 
removed the ``Interim Action'' discussion from the AD; however, the FAA 
may consider further rulemaking if

[[Page 34060]]

a determination is made at a later date that the terminating 
modification should be mandated.

Conclusion

    After careful review of the available data, including the comment 
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 341 airplanes of U.S. registry that will be 
affected by this AD. It will take approximately 2 work hours to 
accomplish the required inspection, at an average labor rate of $60 per 
work hour. Based on these figures, the cost impact of the inspection 
required 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 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 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.
    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, 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 removing amendment 39-10644 (63 FR 
36834, July 8, 1998), and by adding a new airworthiness directive (AD), 
amendment 39-11740, to read as follows:

2000-10-16  Airbus Industrie: Amendment 39-11740. Docket 99-NM-28-
AD. Supersedes AD 98-14-11, Amendment 39-10644.

    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) 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, 
unless the terminating action of paragraph (c) of this AD is 
accomplished. 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.

Optional Terminating Modification

    (c) Modification of the lock bolts of the bolt for the pintle 
pin on the MLG in accordance with Airbus Service Bulletin A320-32-
1213, dated March 21, 2000, constitutes terminating action for the 
requirements of 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 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.


[[Page 34061]]



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.

Incorporation by Reference

    (f) The actions shall be done 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.
    (1) The incorporation by reference of Airbus Service Bulletin 
A320-32-1187, dated June 17, 1998, and Airbus Service Bulletin A320-
32-1187, Revision 01, dated February 17, 1999, is approved by the 
Director of the Federal Register in accordance with 5 U.S.C. 552(a) 
and 1 CFR part 51.
    (2) The incorporation by reference of Airbus All Operator Telex 
(AOT) 32-17, Revision 01, dated November 6, 1997, was approved 
previously by the Director of the Federal Register as of August 12, 
1998 (63 FR 36834, July 8, 1998).
    (3) Copies may be obtained from Airbus Industrie, 1 Rond Point 
Maurice Bellonte, 31707 Blagnac Cedex, France. Copies may be 
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.

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

    (g) This amendment becomes effective on June 30, 2000.

    Issued in Renton, Washington, on May 16, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-12815 Filed 5-25-00; 8:45 am]
BILLING CODE 4910-13-U