[Federal Register Volume 64, Number 162 (Monday, August 23, 1999)]
[Rules and Regulations]
[Pages 45868-45870]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-21365]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96-NM-29-AD; Amendment 39-11259; AD 99-17-11]
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 adopts a new airworthiness directive (AD), 
applicable to certain Airbus Model A319, A320, and A321 series 
airplanes, that 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 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 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 September 27, 1999.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of September 27, 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) to include an airworthiness 
directive (AD) that is applicable to certain Airbus Model A319, A320, 
and A321 series airplanes was published as a supplemental notice of 
proposed rulemaking (NPRM) in the Federal Register on September 15, 
1998 (63 FR 49309). That action proposed to require repetitive 
inspections to detect wear of the inboard flap trunnions; and 
replacement, if necessary. That action also proposed to require 
repetitive inspections to detect wear or debonding of the protective 
half-shells, and corrective actions, if necessary.

Comments Received

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

Request to Approve Terminating Modification

    Two commenters request that the modification described in Airbus 
Service Bulletin A320-27-1117, dated July 31, 1997, be considered as 
terminating action for the repetitive inspections required by the 
proposed AD. One commenter states that the manufacturer has completed 
its in-service evaluation of this service bulletin and has determined 
that the modification is an appropriate terminating action. Another 
commenter, the manufacturer, notes that this modification solution, 
Airbus Modification 26495, has been installed on airplanes in 
production beginning with manufacturer's serial number (MSN) 789.
    The FAA concurs with the commenter's request. Since issuance of the 
supplemental NPRM, the Direction Generale de l'Aviation Civile (DGAC), 
which is the airworthiness authority for France, has advised the FAA 
that accomplishment of the modification described in A320-27-1117 would 
effectively eliminate the need to perform the repetitive inspections, 
and has issued French airworthiness directive 1996-271-092(B) R2, dated 
February 24, 1999, to reflect this finding. The FAA has determined that 
such a modification constitutes appropriate terminating action for the 
repetitive inspections required by this AD, and has revised the 
applicability of the final rule and added a new paragraph (e) to the 
final rule to provide for accomplishment of Airbus Modification 26495 
in production, or Airbus Service Bulletin A320-27-1117, dated July 31, 
1997, or Revision 01, dated June 25, 1999, as an optional terminating 
action for the requirements of this AD.

Service Bulletin Revisions

    Airbus has issued the following Service Bulletin revisions: A320-
27-1108, Revision 02, dated April 17, 1998, and Revision 03, dated June 
25, 1999; and A320-27-1097, Revision 02, dated June 25, 1999. These 
later revisions of the service bulletins describe certain 
administrative changes, and delete the repair previously recommended if 
wear marks are found on the flap trunnions. In lieu of the repair, the 
service bulletin revisions specify accomplishment of the modification 
described in A320-27-1117. The FAA has determined that the actions 
required by this AD may be accomplished in accordance with these later 
revisions of the service bulletins, and has revised the final rule to 
include them as appropriate sources of service information.

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 changes described 
previously. 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

    The FAA estimates that 132 airplanes of U.S. registry will be 
affected by this AD, that it will take approximately 1 work hour per 
airplane to accomplish the required actions, and that the average labor 
rate is $60 per work hour. Based on these figures, the cost impact of 
the AD on U.S. operators is estimated to be $7,920, or $60 per 
airplane, per inspection cycle.
    The cost impact figure discussed above is based on assumptions that 
no operator has yet accomplished any of

[[Page 45869]]

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 substantial direct 
effects 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, in 
accordance with Executive Order 12612, it is determined that this final 
rule does not have sufficient federalism implications to warrant the 
preparation of a Federalism Assessment.
    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 adding the following new 
airworthiness directive:

99-17-11  Airbus Industrie: Amendment 39-11259. Docket 96-NM-29-AD.

    Applicability: Model A319, A320, and A321 series airplanes; 
except airplanes on which Airbus Modification 26495 has been 
installed in production, or on which Airbus Service Bulletin A320-
27-1117, dated July 31, 1997, or Revision 01, dated June 25, 1999, 
has been accomplished; certificated in any category.

    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 (f) 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 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:

Inspections/Corrective Actions

    (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, April 17, 1998, or 
Revision 03, 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 the effective date of 
this AD, 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 the 
effective date of this AD, whichever occurs later.
    (3) For Airbus Model A320 series airplanes on which Airbus 
Modification 22881 has been accomplished, and on which Airbus 
Modification 22841 or the modification specified in Airbus Service 
Bulletin A320-27-1050 has not been accomplished: Inspect within 500 
flight hours after the effective date of this AD.
    (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 the effective date of this AD, 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).
    (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 del'Aviation Civile (or its delegated 
agent).

Optional Terminating Action

    (e) Accomplishment of the modification described in Airbus 
Service Bulletin A320-27-1117, dated July 31, 1997, or Revision 01, 
dated June 25, 1999, constitutes terminating actions for the 
requirements of this AD. Following accomplishment of the 
modification, no further action is required by this AD.

Alternative Methods of Compliance

    (f) 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.

    Note 2: 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

    (g) 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

    (h) Except as provided 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,

[[Page 45870]]

1997; Airbus Service Bulletin A320-27-1108, Revision 02, dated April 
17, 1998; Airbus Service Bulletin A320-27-1108, Revision 0303, 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/or Airbus Service Bulletin A320-27-
1097, Revision 0202, dated June 25, 1999; as applicable. This 
incorporation by reference was approved by the Director of the 
Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 
51. 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 3: The subject of this AD is addressed in French 
airworthiness directives 96-271-092(B) R1, dated October 8, 1997, 
and 1996-271-092(B) R2, dated February 24, 1999.

    (i) This amendment becomes effective on September 27, 1999.

    Issued in Renton, Washington, on August 10, 1999.
D.L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 99-21365 Filed 8-20-99; 8:45 am]
BILLING CODE 4910-13-P