AD 2000-24-02

[Federal Register Volume 65, Number 233 (Monday, December 4, 2000)]
[Rules and Regulations]
[Pages 75603-75605]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 00-30119]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-381-AD; Amendment 39-12009; AD 2000-24-02]
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 to detect 
wear of the inboard flap trunnions, and to detect wear or debonding of 
the protective half-shells; and corrective actions, if necessary. This 
amendment requires accomplishment of the previously optional 
terminating action. 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 
chafing and resultant wear damage on the inboard flap drive trunnions 
or on the protective half-shells, which could result in failure of the 
trunnion primary load path; this would adversely affect the fatigue 
life of the secondary load path and could lead to loss of the flap.

DATES: Effective January 8, 2001.
    The incorporation by reference of certain publications, as listed 
in the regulations, is approved by the Director of the Federal Register 
as of January 8, 2001.
    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 September 27, 1999 (64 FR 45868, August 23, 
1999).

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 99-17-11, 
amendment 39-11259 (64 FR 45868, August 23, 1999), which is applicable 
to certain Airbus Model A319, A320, and A321 series airplanes, was 
published in the Federal Register on September 20, 2000 (65 FR 56814). 
The action proposed to continue to require repetitive inspections to 
detect wear of the inboard flap trunnions, and to detect wear or 
debonding of the protective half-shells; and corrective actions, if 
necessary. The action also proposed to require accomplishment of the 
previously optional terminating action.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were submitted in response 
to the proposal or the FAA's determination of the cost to the public.

Conclusion

    The FAA has determined that air safety and the public interest 
require the adoption of the rule as proposed.

Cost Impact

    There are approximately 132 airplanes of U.S. registry that will be 
affected by this AD.
    The actions that are currently required by AD 99-17-11, and 
retained in this AD, take approximately 1 work hour 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 approximately $7,920, or $60 per airplane, per 
inspection cycle.
    The new actions that are required in this AD will take 
approximately 14 work hours per airplane to accomplish, at an average 
labor rate of $60 per work hour. Required parts will be provided by the 
manufacturer at no cost to the operators. Based on these figures, the 
cost impact of the new requirements of this AD on U.S. operators is 
estimated to be $110,880, or $840 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

[[Page 75604]]

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 amendment 39-11259 (64 FR 
45868, August 23, 1999), and by adding a new airworthiness directive 
(AD), amendment 39-12009, to read as follows:

2000-24-02  Airbus Industrie: Amendment 39-12009. Docket 99-NM-381-
AD. Supersedes AD 99-17-11, Amendment 39-11259.

    Applicability: Model A319, A320, and A321 series airplanes; 
certificated in any category; except airplanes on which Airbus 
Modification 26495 (reference Airbus Service Bulletin A320-27-1117) 
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 (g)(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 chafing and resultant wear damage on the inboard flap 
drive trunnions or on the protective half-shells, which could result 
in failure of the trunnion primary load path, adversely affect the 
fatigue life of the secondary load path, and lead to loss of the 
flap, accomplish the following:

Restatement of Certain Requirements of AD 99-17-11

Inspections

    (a) For airplanes on which a protective half-shell has been 
installed over area 1 of the left or right inboard flap trunnion: 
Perform a detailed visual inspection of the protective half-shell 
(area 1) to detect wear or debonding, and perform a detailed visual 
inspection of the trunnion (area 2) to detect wear at the time 
specified in paragraph (a)(1), (a)(2), or (a)(3) of this AD, as 
applicable; in accordance with Airbus Service Bulletin A320-27-1108, 
Revision 01, dated July 15, 1997, Revision 02, dated April 17, 1998, 
or Revision 03, dated June 25, 1999.
    (1) For Model A319 and Model A320 series airplanes on which 
Airbus Modification 22841 has been installed: Inspect prior to the 
accumulation of 2,500 flight hours after the incorporation of the 
modification, or within 500 flight hours after September 27, 1999 
(the effective date of AD 99-17-11, amendment 39-11259), whichever 
occurs later.
    (2) For Model A321 series airplanes on which Airbus Modification 
23926 has been installed, or on which the repair specified in Airbus 
Service Bulletin A320-27-1097, dated October 5, 1996, or Revision 
01, dated July 15, 1997, has been accomplished; and for Model A320 
series airplanes on which the repair specified in Airbus Service 
Bulletin A320-27-1066, Revision 3, dated October 30, 1996, or 
Revision 4, dated July 15, 1997, has been accomplished: Inspect 
prior to the accumulation of 5,000 flight hours after incorporation 
of the repair or modification, or within 500 flight hours after 
September 27, 1999, whichever occurs later.
    (3) For Airbus Model A320 series airplanes on which Airbus 
Modification 22881 (Airbus Service Bulletin A320-27-1050) has been 
accomplished, and on which Airbus Modification 22841 has not been 
accomplished: Inspect within 500 flight hours after the effective 
date of this new AD.

    Note 2: Paragraph (a)(3) of AD 99-17-11 has been revised to 
correct the description of airplanes affected by that paragraph. 
Since such a revision could result in additional airplanes being 
affected, the compliance time has been restarted from the effective 
date of this AD to allow additional time to accomplish the actions 
required by that paragraph.

    (b) For airplanes on which no protective half-shell is installed 
over area 1 of the left or right inboard flap trunnion: Within 500 
flight hours after September 27, 1999, perform a detailed visual 
inspection of areas 1 and 2 of the inboard flap trunnion to detect 
wear on the trunnion, in accordance with Airbus Service Bulletin 
A320-27-1066, Revision 4, dated July 15, 1997 (for Model A320 series 
airplanes); or A320-27-1097, Revision 01, dated July 15, 1997, or 
Revision 02, dated June 25, 1999 (for Model A321 series airplanes).

Corrective Actions

    (c) Except as provided by paragraph (d) of this AD: Following 
the accomplishment of any inspection required by either paragraph 
(a) or (b) of this AD, perform the follow-on repetitive inspections 
and/or corrective actions, as applicable, in accordance with Airbus 
Service Bulletin A320-27-1066, Revision 4, dated July 15, 1997 (for 
Model A320 series airplanes); A320-27-1097, Revision 01, dated July 
15, 1997, or Revision 02, dated June 25, 1999 (for Model A321 series 
airplanes); or A320-27-1108, Revision 01, dated July 15, 1997, 
Revision 02, dated April 17, 1998, or Revision 03, dated June 25, 
1999 (for Model A319, A320, and A321 series airplanes); as 
applicable; at the compliance times specified in the applicable 
service bulletin.
    (d) If the applicable service bulletin specifies to contact 
Airbus for an appropriate action, prior to further flight, repair in 
accordance with a method approved by either the Manager, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
or the Direction Generale de l'Aviation Civile (or its delegated 
agent).

New Requirements of this AD

Service Bulletin Revisions

    (e) As of the effective date of this new AD, the following 
service bulletin revisions must be used for accomplishment of the 
applicable actions required by paragraphs (a), (b), and (c) of this 
AD:
    (1) Airbus Service Bulletin A320-27-1108, Revision 04, dated 
November 22, 1999.
    (2) Airbus Service Bulletin A320-27-1066, Revision 5, dated June 
25, 1999.

Terminating Modification

    (f) Within 18 months after the effective date of this AD, modify 
the sliding panel driving mechanism of the flap drive trunnions, in 
accordance with Airbus Service Bulletin A320-27-1117, Revision 02, 
dated January 18, 2000. This modification constitutes terminating 
action for the repetitive inspections required by this AD.

    Note 3: Accomplishment of the modification required by paragraph 
(f) of this

[[Page 75605]]

AD prior to the effective date of this AD in accordance with Airbus 
Service Bulletin A320-27-1117, dated July 31, 1997, or Revision 01, 
dated June 25, 1999, is acceptable for compliance with that 
paragraph.

Alternative Methods of Compliance

    (g)(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. 
Operators shall submit 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 99-17-11, amendment 39-11259, are approved as 
alternative methods of compliance with this AD.

    Note 4: 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

    (h) 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

    (i) Except as required by paragraph (d) of this AD, the actions 
shall be done in accordance with Airbus Service Bulletin A320-27-
1108, Revision 01, dated July 15, 1997; Airbus Service Bulletin 
A320-27-1108, Revision 02, dated April 17, 1998; Airbus Service 
Bulletin A320-27-1108; Revision 03, dated June 25, 1999; Airbus 
Service Bulletin A320-27-1066, Revision 4, dated July 15, 1997; 
Airbus Service Bulletin A320-27-1097, Revision 01, dated July 15, 
1997; Airbus Service Bulletin A320-27-1097, Revision 02, dated June 
25, 1999; Airbus Service Bulletin A320-27-1108, Revision 04, dated 
November 22, 1999; Airbus Service Bulletin A320-27-1066, Revision 5, 
dated June 25, 1999; and Airbus Service Bulletin A320-27-1117, 
Revision 02, dated January 18, 2000; as applicable.
    (1) The incorporation by reference of Airbus Service Bulletin 
A320-27-1108, Revision 04, dated November 22, 1999; Airbus Service 
Bulletin A320-27-1066, Revision 5, dated June 25, 1999; and Airbus 
Service Bulletin A320-27-1117, Revision 02, dated January 18, 2000, 
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 Service Bulletin 
A320-27-1108, Revision 01, dated July 15, 1997; Airbus Service 
Bulletin A320-27-1108, Revision 02, dated April 17, 1998; Airbus 
Service Bulletin A320-27-1108; Revision 03, dated June 25, 1999; 
Airbus Service Bulletin A320-27-1066, Revision 4, dated July 15, 
1997; Airbus Service Bulletin A320-27-1097, Revision 01, dated July 
15, 1997; and Airbus Service Bulletin A320-27-1097, Revision 02, 
dated June 25, 1999, was approved previously by the Director of the 
Federal Register as of September 27, 1999 (64 FR 45868, August 23, 
1999).
    (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 5: The subject of this AD is addressed in French 
airworthiness directive 1996-271-092(B) R3, dated August 11, 1999.

Effective Date

    (j) This amendment becomes effective on January 8, 2001.

    Issued in Renton, Washington, on November 20, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-30119 Filed 12-1-00; 8:45 am]
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