[Federal Register Volume 62, Number 100 (Friday, May 23, 1997)]
[Rules and Regulations]
[Pages 28324-28325]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-12857]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 96-NM-106-AD; Amendment 39-10030; AD 97-11-01]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A320 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to certain Airbus Model A320 series airplanes, that requires
an initial inspection of fastener holes on certain outer frames of the
fuselage to detect fatigue cracking, and modification of this area by
cold expanding these holes and installing oversized fasteners. This
amendment is prompted by a report from the manufacturer indicating
that, during full-scale fatigue testing of the test article, fatigue
cracking was detected in the area where the center fuselage joins the
wing. The actions specified by this AD are intended to prevent fatigue
cracking and consequent reduced structural integrity of this area,
which could lead to rapid depressurization of the fuselage.
DATES: Effective June 27, 1997.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of June 27, 1997.
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 Backman, Aerospace Engineer,
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2797; 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 series
airplanes was published in the Federal Register on February 20, 1997
(62 FR 7727). That action proposed to require an initial eddy current
rotation probe inspection to detect fatigue cracking in certain
fastener holes in the area where the center fuselage joins the wing,
and a modification to improve the resistance of this area to fatigue
cracking.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the two comments received.
Both commenters support the proposed rule.
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 as proposed.
Cost Impact
The FAA estimates that 24 Airbus Model A320 series airplanes of
U.S. registry will be affected by this AD.
It will take approximately 25 work hours per airplane to accomplish
the required actions, at an average labor rate of $60 per work hour.
Required parts will cost approximately $557 per airplane. Based on
these figures, the cost impact of the AD on U.S. operators is estimated
to be $49,368, or $2,057 per airplane.
The cost impact figure discussed above is 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
[[Page 28325]]
``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:
97-11-01 Airbus Industrie: Amendment 39-10030. Docket 96-NM-106-AD.
Applicability: Model A320 series airplanes as listed in Airbus
Service Bulletin A320-53-1026, dated August 5, 1994; on which
modifications 21281P1495 and 21680P1818 have not been installed;
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 (e) 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 fatigue cracking in the area where the center
fuselage joins the wing, which could reduce the structural integrity
of this area and consequently result in rapid decompression of the
fuselage, 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, perform an eddy current rotating probe inspection to
detect fatigue cracking in the fastener holes of the outer frame
flanges of left and right fuselage frames 37 through 41, adjacent to
Stringer 23, in accordance with Airbus Service Bulletin A320-53-
1026, dated August 5, 1994.
Note 2: Prior to the effective date of this AD, accomplishment
of any modification in accordance with Airbus Service Bulletin A320-
53-1025, dated August 5, 1994, is considered acceptable for
compliance with the modification requirements of paragraphs (b),
(c)(1)(i), (c)(2) and (d) of this AD.
(b) If the inspection required by paragraph (a) of this AD
detects no cracking in any hole: Prior to the accumulation of 6,000
landings after this inspection, modify each hole in accordance with
Paragraph 2.B.(5) of Airbus Service Bulletin A320-53-1025, Revision
1, dated November 24, 1994. Thereafter, no further action is
required by this AD.
(c) If the inspection required by paragraph (a) of this AD
detects any cracking in no more than one hole per frame cap,
accomplish the requirements of paragraphs (c)(1) and (c)(2) of this
AD:
(1) Prior to further flight, repair this cracked hole and
conduct another rotating probe inspection of this hole to detect
cracking, in accordance with Paragraph 2.B.(6) of Airbus Service
Bulletin A320-53-1025, Revision 1, dated November 24, 1994.
(i) If no cracking of this repaired hole is detected: Prior to
further flight, modify this hole in accordance with Paragraph
2.B.(6)(c) of this service bulletin. Thereafter, no further action
with regard to this hole is required by this AD.
(ii) If any cracking of this repaired hole is detected: Prior to
further flight, repair this hole in a manner approved by the
Manager, Standardization Branch, ANM-113, FAA, Transport Airplane
Directorate. Thereafter, no further action with regard to this hole
is required by this AD.
(2) Prior to the accumulation of 6,000 landings after the
inspection required by paragraph (a) of this AD; modify all other
holes in accordance with Paragraph 2.B.(5) of Airbus Service
Bulletin A320-53-1025, Revision 1, dated November 24, 1994.
Thereafter, no further action is required by this AD with respect to
these holes.
(d) If the inspection required by paragraph (a) of this AD
detects any cracking in more than one hole per frame cap, or if this
inspection detects any cracking in any frame: Prior to further
flight, repair the discrepant area in a manner approved by the
Manager, Standardization Branch, ANM-113; and modify all other holes
in accordance with Paragraph 2.B.(5) of Airbus Service Bulletin
A320-53-1025, Revision 1, dated November 24, 1994. Thereafter, no
further action is required by this AD.
(e) 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, Standardization Branch, ANM-113.
Operators shall submit their requests through an appropriate FAA
Principal Maintenance Inspector, who may add comments and then send
it to the Manager, Standardization Branch, ANM-113.
Note 3: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Standardization Branch, ANM-113.
(f) 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.
(g) The actions shall be done in accordance with Airbus Service
Bulletin A320-53-1026, dated August 5, 1994; and Airbus Service
Bulletin A320-53-1025, Revision 1, dated November 24, 1994. Airbus
Service Bulletin A320-53-1025, Revision 1, dated November 24, 1994,
contains the following list of effective pages:
------------------------------------------------------------------------
Revision level
Page No. shown on page Date shown on page
------------------------------------------------------------------------
1-12, 17....................... 1.............. November 24, 1994.
13-16, 18, 19.................. Original....... August 5, 1994.
------------------------------------------------------------------------
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.
(h) This amendment becomes effective on June 27, 1997.
Issued in Renton, Washington, on May 12, 1997.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 97-12857 Filed 5-22-97; 8:45 am]
BILLING CODE 4910-13-U
