[Federal Register Volume 63, Number 110 (Tuesday, June 9, 1998)]
[Rules and Regulations]
[Pages 31345-31346]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-15134]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 96-NM-184-AD; Amendment 39-10573; AD 98-12-18]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A320-111, -211, and -231
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 A320-111, -211, and -231 series
airplanes, that requires repetitive inspections for cracking in the
transition and pick-up angles in the lower part of the center fuselage
area, and corrective action, if necessary. This amendment also provides
for an optional terminating modification for the repetitive inspection
requirements. This amendment is prompted by the issuance of mandatory
continuing airworthiness information by a foreign civil airworthiness
authority. The actions specified by this AD are intended to detect and
correct fatigue cracking in the transition and pick-up angles of the
lower part of the center fuselage, which could result in reduced
structural integrity of the wing-fuselage support and fuselage pressure
vessel.
DATES: Effective July 14, 1998.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of July 14, 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) to include an airworthiness
directive (AD) that is applicable to certain Airbus Model A320-111, -
11, and -231 series airplanes was published in the Federal Register on
November 19, 1997 (62 FR 61704). That action proposed to require
repetitive inspections for cracking in the transition and pick-up
angles in the lower part of the center fuselage area, and corrective
action, if necessary. That action also proposed to provide for an
optional terminating modification for the repetitive inspection
requirements.
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.
Two commenters support the proposed rule.
One commenter supports the intent of the proposed rule, but
identifies a redundancy that appears in paragraph (a)(2)(i)(A) of the
proposed AD. The commenter notes that the repetitive inspection
requirements of this paragraph specify accomplishment of both a visual
and a rotating probe (eddy current) inspection, whereas the original
requirement was only for an eddy current inspection. Since the eddy
current inspection provides a greater detailed inspection than a visual
inspection, the commenter states that the visual inspection should not
be necessary. The FAA concurs and has revised paragraph (a)(2)(i)(A) of
the final rule accordingly.
Additionally, paragraphs (a)(1)(i)(B), (a)(1)(ii), and (a)(2)(i)(B)
of the final rule have been revised to cite only Revision 2 of Airbus
Service Bulletin A320-53-1027 for accomplishment of certain actions.
Revision 2 contains no substantive differences from the original or
Revision 1 of the service bulletin. A ``NOTE'' has been added to the
final rule to give credit to operators who may have previously
accomplished the required actions in accordance with these earlier
versions of the service bulletin.
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
The FAA estimates that 24 airplanes of U.S. registry will be
affected by this AD.
It will take approximately 9 work hours per airplane to accomplish
the required inspections, at an average labor rate of $60 per work
hour. Based on these figures, the cost impact of the inspections
required by this AD on U.S. operators is estimated to be $12,960, or
$540 per airplane, per inspection cycle.
It will take approximately 10 work hours per airplane to accomplish
the required modification, at an average labor rate of $60 per work
hour. Required parts will cost approximately $2,895 per airplane. Based
on these figures, the cost impact of the modification required by this
AD on U.S. operators is estimated to be $83,880, or $3,495 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.
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
[[Page 31346]]
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:
98-12-18 Airbus Industrie: Amendment 39-10573. Docket 96-NM-184-AD.
Applicability: Model A320-111, -211, and -231 series airplanes,
manufacturer's serial numbers 002 through 008 inclusive, 010 through
014 inclusive, 016 through 078 inclusive, and 080 through 107
inclusive; certificated in any category.
Note 1: This AD applies to each airplane identified in the
preceding applicability provision, regardless of whether it has been
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 (b) 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 reduced structural integrity of the wing-
fuselage support and fuselage pressure vessel resulting from
structural fatigue cracking in the transition and pick-up angles,
accomplish the following:
(a) Prior to the accumulation of 16,000 total landings, or
within 6 months after the effective date of this AD, whichever
occurs later, accomplish paragraphs (a)(1) and (a)(2) of this AD, in
accordance with Airbus Service Bulletin A320-53-1028, dated March 1,
1994.
(1) Perform a visual inspection to detect cracks of the
transition angle, in accordance with the service bulletin.
(i) If no crack is detected during the visual inspection
required by paragraph (a)(1) of this AD, accomplish either paragraph
(a)(1)(i)(A) or paragraph (a)(1)(i)(B) of this AD.
(A) Repeat the visual inspection thereafter at intervals not to
exceed 12,000 landings. Or
(B) Prior to further flight, modify the center fuselage in
accordance with Airbus Service Bulletin A320-53-1027, Revision 2,
dated June 8, 1995. Accomplishment of the modification constitutes
terminating action for the repetitive inspection requirements of
paragraph (a)(1)(i)(A) of this AD.
(ii) If any crack is detected during the visual inspection
required by paragraph (a)(1) of this AD, prior to further flight,
replace the transition angle with a new transition angle, in
accordance with Airbus Service Bulletin A320-53-1027, Revision 2,
dated June 8, 1995.
(2) Perform a rotating probe inspection to detect cracks of the
pick-up angle, in accordance with the service bulletin.
(i) If no crack is detected during the rotating probe inspection
required by paragraph (a)(2) of this AD, accomplish either paragraph
(a)(2)(i)(A) or (a)(2)(i)(B) of this AD.
(A) Repeat the rotating probe inspection thereafter at intervals
not to exceed 12,000 landings. Or
(B) Prior to further flight, modify the center fuselage in
accordance with Airbus Service Bulletin A320-53-1027, Revision 2,
dated June 8, 1995. Accomplishment of the modification constitutes
terminating action for the repetitive inspection requirements of
paragraph (a)(2)(i)(A) of this AD.
(ii) If any crack is detected and it is less than 1.9 mm in
length, prior to further flight, accomplish the applicable
corrective actions specified in the service bulletin. For holes that
have not been modified in accordance with the service bulletin,
repeat the rotating probe inspection thereafter at intervals not to
exceed 12,000 landings.
(iii) If any crack is detected and it is 1.9 mm or greater in
length, prior to further flight, repair it in accordance with the
method approved by the Manager, International Branch, ANM-116, FAA,
Transport Airplane Directorate.
Note 2: Accomplishment of the modification or replacement
required by paragraph (a) of this AD in accordance with Airbus
Service Bulletin A320-53-1027, dated March 1, 1994, or Revision 1,
dated September 5, 1994, prior to the effective date of this AD, is
acceptable for compliance with this paragraph.
(b) 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 their requests 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.
(c) 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.
(d) The inspections shall be done in accordance with Airbus
Service Bulletin A320-53-1028, dated March 1, 1994. The modification
and replacement shall be done in accordance with Airbus Service
Bulletin A320-53-1027, Revision 2, dated June 8, 1995. Airbus
Service Bulletin A320-53-1027, Revision 2, dated June 8, 1995,
contains the following list of effective pages:
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Revision
Page No. level shown Date shown on page
on page
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1-6, 8, 10-16, 19............. 2............ June 8, 1995.
7, 17, 18, 20................. Original..... March 1, 1994.
9............................. 1............ September 5, 1994.
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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 4: The subject of this AD is addressed in French
airworthiness directive 95-097-065(B), dated May 24, 1995.
(e) This amendment becomes effective on July 14, 1998.
Issued in Renton, Washington, on June 2, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-15134 Filed 6-8-98; 8:45 am]
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