[Federal Register Volume 63, Number 54 (Friday, March 20, 1998)]
[Rules and Regulations]
[Pages 13489-13491]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-6758]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 95-NM-216-AD; Amendment 39-10398; AD 98-06-20]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A320 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 A320 series airplanes, that
currently requires inspections to detect cracking of certain floor
beams and side box-beams, and repair of cracks; and modification of the
pressure floor. That AD was prompted by results of a full-scale fatigue
test. This amendment adds a one-time inspection to verify proper
clearance between the fasteners of the reinforcement bracket and the
bellcrank of the free-fall extension system of the main landing gear
(MLG) and its associated tie rod attachment nut. This amendment also
adds a requirement for a new improved modification of the pressure
floor. The actions specified by this AD are intended to prevent reduced
structural integrity of the fuselage, restricted operation of the MLG
free-fall system and, consequently, reduced ability to use the MLG
during an emergency.
DATES: Effective April 24, 1998.
The incorporation of certain publications, as listed in the
regulations, is approved by the Director of the Federal Register as of
April 24, 1998.
The incorporation by reference of Airbus Industrie Service Bulletin
A320-53-1024, dated September 23, 1992, as listed in the regulations,
was approved previously by the Director of the Federal Register as of
August 23, 1993 (58 FR 39440, July 23, 1993).
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 93-14-04,
amendment 39-8628 (58 FR 39440, July 23, 1993), which is applicable to
certain Airbus Model A320 series airplanes, was published as a
supplemental notice of proposed rulemaking (NPRM) in the Federal
Register on March 12, 1997 (62 FR 11388). The action proposed to
continue to require inspections to detect cracking of the floor beams
and the side box-beams, and repair of cracks. The action also proposed
to add a one-time inspection to verify proper clearance between the
fasteners of the reinforcement bracket and the bellcrank of the free-
fall extension system of the main landing gear (MLG) and its associated
tie rod attachment nut. In addition, the action proposed to add a
requirement for a new improved modification of the pressure floor.
Comments
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the single comment received.
The commenter requests that paragraph (c)(1)(ii) of the
supplemental NPRM be revised to include an option to rework the
bellcrank just like paragraph (c)(1)(iii)(B) of the supplemental NPRM.
The commenter points out that the Direction Generale de l'Aviation
Civile (DGAC), which is the airworthiness authority for France, has
included this rework option in its revised French airworthiness
directive (CN) 96-053-77(B)R1, dated June 5, 1996.
The FAA concurs. The FAA has reviewed the subject French
airworthiness directive, and has revised paragraph (c)(1)(ii) of this
final rule to include an option to rework the bellcrank lever and
fasteners, and reinstall the reinforcement bracket fasteners, which is
identical to the requirements of paragraph (c)(1)(iii)(B) of the AD.
Conclusion
After careful review of the available data, including the comment
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
There are approximately 24 Airbus Model A320 series airplanes of
U.S. registry that will be affected by this AD.
The inspections that are currently required by AD 93-14-04 take
approximately 37 work hours 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 inspections on U.S. operators is
estimated to be $53,280, or $2,220 per airplane.
The new inspection that is required by this AD action will take
approximately 11 work hours per airplane to accomplish, at an average
labor rate of $60 per work hour. Based on these figures, the cost
impact of the new inspection required by this AD on U.S. operators is
estimated to be $15,840, or $660 per airplane.
The new modification that is required by this AD action will take
approximately 142 work hours per airplane to accomplish, at an average
labor rate of $60 per work hour. Required parts will be supplied by the
manufacturer at no cost to the operators. Based on these figures, the
cost impact of the modification required by this AD on U.S. operators
is estimated to be $204,480, or $8,520 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
[[Page 13490]]
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 removing amendment 39-8628 (58 FR
39440, July 23, 1993), and by adding a new airworthiness directive
(AD), amendment 39-10398, to read as follows:
98-06-20 Airbus Industrie: Amendment 39-10398. Docket 95-NM-216-AD.
Supersedes AD 93-14-04, Amendment 39-8628.
Applicability: Model A320 series airplanes, manufacturer's
serial numbers 002 through 008 inclusive, 010 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 (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 prevent reduced structural integrity of the fuselage,
restricted operation of the main landing gear (MLG) free-fall
system, and, consequently, reduced ability to use the MLG during an
emergency, accomplish the following:
(a) Prior to the accumulation of 12,000 total landings, or
within 6 months after August 23, 1993 (the effective date of AD 93-
14-04, amendment 39-8628), whichever occurs later, accomplish the
requirements of paragraphs (a)(1) and (a)(2) of this AD, in
accordance with Airbus Service Bulletin A320-53-1024, dated
September 23, 1992, or Revision 1, dated March 31, 1994. As of the
effective date of this new AD, only Revision 1 of this service
bulletin shall be used.
(1) Conduct an eddy current inspection to detect cracking around
the fastener/bolt holes at the top horizontal flange of the floor
beams and side box-beams, at the two sides of the pressure floor,
and at the vertical integral stiffener of the side box-beams; and
(2) Conduct a detailed visual inspection to detect cracking
around the fastener/bolt holes at the fillet radius and riveted area
of the top outboard flange of the side box-beam, and at the flange-
corner radius of the slanted inboard flange of the side box-beam and
fittings.
(b) If any crack is detected during the inspections required by
paragraph (a) of this AD, prior to further flight, repair the crack
in accordance with a method approved by the Manager, International
Branch, ANM-116, FAA, Transport Airplane Directorate.
(c) For airplanes on which the modification specified in Airbus
Service Bulletin A320-53-1023, dated September 23, 1992, as amended
by Service Bulletin Change Notice 0A, dated January 20, 1993;
Revision 1, dated March 23, 1993; Revision 2, dated October 22,
1993; Revision 3, dated March 18, 1994; Revision 4, dated September
30, 1994; Revision 5, dated February 28, 1995; or Revision 6, dated
September 4, 1995; has been accomplished: Accomplish paragraphs
(c)(1) and (c)(2) of this AD.
(1) Prior to the accumulation of 1,000 landings after the
effective date of this AD, perform a one-time inspection to verify
proper clearance between the fasteners of the reinforcement bracket
and the bellcrank of the free-fall extension system of the MLG and
its associated tie rod attachment nut, in accordance with Airbus All
Operators Telex (AOT) 53-08, Revision 01, dated January 15, 1996.
(i) If the minimum clearance is greater than 3 mm (0.118 inch)
and no evidence of interference is detected, within 60 months
following accomplishment of the inspection required by paragraph
(c)(1) of this AD, reinstall the reinforcement bracket fasteners in
accordance with Airbus Service Bulletin A320-53-1023, Revision 7,
dated November 3, 1995.
(ii) If the minimum clearance is 3 mm (0.118 inch) or less, and
no evidence of interference is detected, within 18 months following
accomplishment of the inspection required by paragraph (c)(1) of
this AD, accomplish either paragraph (c)(1)(ii)(A) or (c)(1)(ii)(B)
of this AD.
(A) Reinstall the reinforcement bracket fasteners in accordance
with Airbus Service Bulletin A320-53-1023, Revision 7, dated
November 3, 1995; or
(B) Rework the bellcrank lever and fasteners in accordance with
Airbus AOT 53-08, Revision 01, dated January 15, 1996. Within 60
months following accomplishment of the rework, reinstall the
reinforcement bracket fasteners in accordance with Airbus Service
Bulletin A320-53-1023, Revision 7, dated November 3, 1995.
(iii) If any interference is detected, prior to further flight,
accomplish either paragraph (c)(1)(iii)(A) or (c)(1)(iii)(B) of this
AD.
(A) Reinstall the reinforcement bracket fasteners in accordance
with Airbus Service Bulletin A320-53-1023, Revision 7, dated
November 3, 1995; or
(B) Rework the bellcrank lever and fasteners in accordance with
Airbus AOT 53-08, Revision 01, dated January 15, 1996. Within 60
months following accomplishment of the rework, reinstall the
reinforcement bracket fasteners in accordance with Airbus Service
Bulletin A320-53-1023, Revision 7, dated November 3, 1995.
(2) Prior to the accumulation of 24,000 total landings, or
within 6 months after the effective date of this AD, whichever
occurs later, modify the pressure floor at section 15 of the
fuselage in accordance with Airbus Service Bulletin A320-53-1023,
Revision 7, dated November 3, 1995. Accomplishment of the
modification terminates the requirements of this AD.
(d) For airplanes on which the modification specified in Airbus
Service Bulletin A320-53-1023, dated September 23, 1992, as amended
by Service Bulletin Change Notice 0A, dated January 20, 1993;
Revision 1, dated March 23, 1993; Revision 2, dated October 22,
1993; Revision 3, dated March 18, 1994; Revision 4, dated September
30, 1994; Revision 5, dated February 28, 1995; or Revision 6, dated
September 4, 1995; has not been accomplished: Prior to the
accumulation of 18,000 total landings, or within 6 months after the
effective date of this AD, whichever occurs later, modify the
pressure floor at section 15 of the fuselage in accordance with
Airbus Service Bulletin A320-53-1023, Revision 7, dated November 3,
1995. Accomplishment of the modification terminates the requirements
of this AD.
(e) Accomplishment of the modification of the pressure floor at
section 15 of the fuselage in accordance with Airbus Service
Bulletin A320-53-1023, Revision 7, dated November 3, 1995,
constitutes terminating action for the requirements of this AD.
(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, Manager, International Branch, ANM-
116, FAA, Transport Airplane Directorate. 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.
[[Page 13491]]
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.
(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.
(h) The actions shall be done in accordance with Airbus Service
Bulletin A320-53-1024, dated September 23, 1992; Airbus Service
Bulletin A320-53-1024, Revision 1, dated March 31, 1994; Airbus All
Operators Telex (AOT) 53-08, Revision 01, dated January 15, 1996;
and Airbus Service Bulletin A320-53-1023, Revision 7, dated November
3, 1995; as applicable. Revision 7 of Airbus Service Bulletin A320-
53-1023 contains the following list of effective pages:
------------------------------------------------------------------------
Revision
level
Page No. shown on Date shown on page
page
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1, 15-55....................... 7 November 3, 1995.
2-14........................... 6 September 4, 1995.
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The incorporation by reference of Airbus Industrie Service
Bulletin A320-53-1024, dated September 23, 1992, as listed in the
regulations, was approved previously by the Director of the Federal
Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51 as of
August 23, 1993 (58 FR 39440, July 23, 1993). The incorporation by
reference of the remainder of the service documents listed above is
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 (CN's) 92-205-033(B)R1, dated June 22,
1994, and 96-053-077(B)R1, dated June 5, 1996.
(i) This amendment becomes effective on April 24, 1998.
Issued in Renton, Washington, on March 10, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-6758 Filed 3-19-98;8:45 am]
BILLING CODE 4910-13-U
