[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]
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