AD 2002-06-01

[Federal Register Volume 67, Number 78 (Tuesday, April 23, 2002)]
[Rules and Regulations]
[Pages 19659-19661]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 02-9573]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-338-AD; Amendment 39-12677; AD 2002-06-01]
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 two existing airworthiness 
directives (ADs), 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 an optional 
terminating action. This amendment cancels the requirements of the 
first AD, continues the requirements of the second AD, and requires the 
previously optional terminating action that the second AD provides. 
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 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: Effective May 28, 2002.
    The incorporation by reference of Airbus Service Bulletin A320-32-
1213, Revision 02, dated February 9, 2001, as listed in the 
regulations, is approved by the Director of the Federal Register as of 
May 28, 2002.
    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 June 30, 2000 (65 FR 34059, May 26, 2000).
    The incorporation by reference of Airbus All Operator Telex (AOT) 
32-17, Revision 01, dated November 6, 1997, 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: 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: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 96-10-18, 
amendment 39-9625 (61 FR 24690, May 16, 1996), which is applicable to 
certain Airbus Model A320-111, -211, -212, and -231 series airplanes; 
and AD 2000-10-16, amendment 39-11740 (65 FR 34059, May 26, 2000), 
which is applicable to certain Airbus Model A319, A320, and A321 series 
airplanes;

[[Page 19660]]

was published in the Federal Register on November 23, 2001 (66 FR 
58684). The action proposed to cancel the requirements of the first AD, 
and continue to require the second AD's repetitive inspections for 
discrepancies of the lock bolt for the pintle pin on the main landing 
gear (MLG), follow-on corrective actions if necessary, and retorquing 
of the forward pintle pin lock bolt for certain airplanes. The action 
also proposed to require the previously optional terminating action 
that was provided for in the second AD.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received from a single commenter. The commenter generally 
supports the intent of the proposed rule, and has no objection to the 
FAA's proposal to mandate the terminating action, though the commenter 
believes that the repetitive inspections for discrepancies of the lock 
bolt for the pintle pin on the MLG are sufficient to ensure safety.

Correct Cost Impact Estimate

    The commenter points out that the proposed rule incorrectly 
estimates the cost impact of the terminating action. While the proposed 
rule estimates the parts cost as $540 per airplane, the actual cost is 
$540 per MLG leg, for a total parts cost of $1,080 per airplane. We 
concur with the commenter and have revised the Cost Impact section of 
this final rule accordingly.

Conclusion

    After careful review of the available data, including the comments 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule with the change previously 
described. The FAA has determined that this change will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.

Cost Impact

    There are approximately 341 Model A319, A320, and A321 series 
airplanes of U.S. registry affected by this 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 required by this AD will take approximately 
3 work hours per airplane to accomplish, at an average labor rate of 
$60 per work hour. Required parts will cost approximately $1,080 per 
airplane. Based on these figures, the cost impact of the new 
requirements of this AD on U.S. operators is estimated to be $429,660, 
or $1,260 per airplane.
    The cost impact figures discussed above are 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. 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 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 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), amendment 39-12677, to read 
as follows:

2002-06-01 Airbus Industrie: Amendment 39-12677. 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 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

[[Page 19661]]

(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, Revision 1, 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 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 
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 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.

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; 
and Airbus Service Bulletin A320-32-1213, Revision 02, dated 
February 9, 2001; as applicable.
    (1) The incorporation by reference of Airbus Service Bulletin 
A320-32-1213, Revision 02, dated February 9, 2001, 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 Airbus Service Bulletin A320-
32-1187, dated June 17, 1998; and Airbus Service Bulletin A320-32-
1187, Revision 01, dated February 17, 1999; was approved previously 
by the Director of the Federal Register, as of June 30, 2000 (65 FR 
34059, May 26, 2000).
    (3) 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).
    (4) Copies of any of these service documents 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 6: The subject of this AD is addressed in French 
airworthiness directive 2000-428-153(B), Revision 1, dated November 
29, 2000.

Effective Date

    (g) This amendment becomes effective on May 28, 2002.

    Issued in Renton, Washington, on April 11, 2002.
Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 02-9573 Filed 4-22-02; 8:45 am]
BILLING CODE 4910-13-U