[Federal Register Volume 63, Number 200 (Friday, October 16, 1998)]
[Rules and Regulations]
[Pages 55515-55517]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-27460]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-NM-74-AD; Amendment 39-10838; AD 98-21-30]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300, A310, and A300-600
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 A300 series airplanes and all Model
A310 and A300-600 series airplanes, that requires repetitive
inspections for wear damage of the aft attachment fittings of the
articulated seats and dummy tracks in the passenger compartment; and
repair, 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 wear damage of the aft attachment fittings of the
articulated seats and dummy tracks. Such wear damage could cause the
floor panels to sag and result in failure of flight control systems and
consequent reduced controllability of the airplane.
DATES: Effective November 20, 1998.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of November 20, 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;
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 A300 series
airplanes and all Model A310 and A300-600 series airplanes was
published in the Federal Register on April 20, 1998 (63 FR 19425). That
action proposed to require repetitive inspections for wear damage of
the aft attachment fittings of the articulated seats and dummy tracks
in the passenger compartment; and repair, if necessary.
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.
Request To Revise Repair Criteria
The commenter, an operator, suggests that repair is not necessary
for wear damage of 1 mm or less. (The proposed AD would have required
repair of any damage.) The commenter reports that its current repair
procedures, which have been approved by Airbus and the French
airworthiness authority, involve repair only when the wear damage
exceeds 1 mm. The commenter notes that the service bulletin cited in
the proposed AD provides sliding wear/repair limits that allow
operators the option to either repair wear damage of 2 mm or less, or
continue to inspect until the wear damage exceeds 2 mm. The commenter
also states that a wear rate of about 0.1 mm per 1,000 flight cycles is
considered normal. Therefore, in order to comply with the AD as
proposed, the commenter anticipates that all of its tracks/fittings
would require repair for minor wear or replacement because of those
normal wear conditions, at an estimated cost of $800,000.
The FAA concurs. Based on information provided by the commenter and
clarification provided by the manufacturer and the French airworthiness
authority, the FAA has determined that such an adjustment of the repair
criteria will represent an appropriate option to operators and still
maintain an acceptable level of safety. Paragraphs (c) and (d) of the
final rule have been revised accordingly. However, the FAA finds that
immediate repair of wear damage that exceeds 1 mm is necessary to
maintain an adequate level of safety.
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 changes described
previously. The FAA has determined that these changes will
[[Page 55516]]
neither increase the economic burden on any operator nor increase the
scope of the AD.
Cost Impact
The FAA estimates that 126 airplanes of U.S. registry will be
affected by this AD, that it will take approximately 48 work hours per
airplane to accomplish the required inspection, 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 $362,880, or
$2,880 per airplane, per inspection cycle.
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 ``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:
98-21-30 Airbus Industrie: Amendment 39-10838. Docket 98-NM-74-AD.
Applicability: Model A300 series airplanes on which Airbus
Modification 3599 or 3135 (reference Airbus Service Bulletin A300-
53-0188) has been accomplished, and all Model A310 and A300-600
series airplanes; 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 wear damage of the aft attachment fittings
of the articulated seats and dummy tracks in the passenger
compartment, which could cause the floor panels to sag and result in
failure of flight control systems and consequent reduced
controllability of the airplane, accomplish the following:
(a) Perform a detailed visual inspection for wear damage of the
aft attachment fittings of the articulated seats and dummy tracks in
the passenger compartment, in accordance with Airbus Service
Bulletins A300-53-0329, Revision 01 (for Airbus Model A300 series
airplanes); A300-53-6105, Revision 01 (for Airbus Model A300-600
series airplanes); or A310-53-2101, Revision 01 (for Airbus Model
A310 series airplanes), all dated October 17, 1997; at the
applicable time specified in paragraph (a)(1) or (a)(2) of this AD.
(1) For airplanes that have accumulated less than 12,000 total
flight cycles as of the effective date of this AD: Inspect prior to
the accumulation of 6,000 total flight cycles, or within 18 months
after the effective date of this AD, whichever occurs later.
(2) For airplanes that have accumulated 12,000 or more total
flight cycles as of the effective date of this AD: Inspect within 12
months after the effective date of this AD.
(b) If no wear damage is detected during the inspection required
by paragraph (a) of this AD, repeat the detailed visual inspection
thereafter at intervals not to exceed 6,000 flight cycles.
(c) If any wear damage measuring 1 mm (0.039 in.) or less is
detected during the inspection required by paragraph (a) of this AD,
accomplish either paragraph (c)(1) or (c)(2) of this AD, in
accordance with Airbus Service Bulletin A300-53-0329, Revision 01
(for Airbus Model A300 series airplanes); A300-53-6105, Revision 01
(for Airbus Model A300-600 series airplanes); or A310-53-2101,
Revision 01 (for Airbus Model A310 series airplanes); all dated
October 17, 1997; as applicable.
(1) Repeat the inspection required by paragraph (a) of this AD
at the interval specified in Figure 1, Sheet 1, of the applicable
service bulletin, for the depth of wear damage detected. Or,
(2) Prior to further flight, repair the wear damage. Thereafter,
repeat the inspection required by paragraph (a) of this AD at
intervals not to exceed 6,000 flight cycles.
(d) If any wear damage measuring more than 1 mm (0.039 in.), and
less than or equal to 2 mm (0.078 in.), is detected during the
inspection required by paragraph (a) of this AD: Prior to further
flight, repair in accordance with Airbus Service Bulletin A300-53-
0329, Revision 01 (for Airbus Model A300 series airplanes); A300-53-
6105, Revision 01 (for Airbus Model A300-600 series airplanes); or
A310-53-2101, Revision 01 (for Airbus Model A310 series airplanes);
all dated October 17, 1997; as applicable. Repeat the inspection
thereafter at intervals not to exceed 6,000 flight cycles.
(e) If any wear damage measuring more than 2 mm (0.078 in.) is
detected during the inspection required by paragraph (a) of this AD,
prior to further flight, repair in accordance with a method approved
by the Manager, International Branch, ANM-116, FAA, Transport
Airplane Directorate. Repeat the visual inspection thereafter at
intervals not to exceed 6,000 flight cycles.
(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, FAA,
Transport Airplane Directorate. Operators shall submit their
requests through an appropriate FAA Principal Maintence 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.
(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) Except as provided by paragraph (e) of this AD, the actions
shall be done in accordance with Airbus Service Bulletin A300-53-
0329, Revision 01, dated October 17, 1997; Airbus Service Bulletin
A300-53-6105, Revision 01, dated October 17, 1997; or A310-53-2101,
Revision 01, dated October
[[Page 55517]]
17, 1997; 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 directive 97-116-222(B), dated May 21, 1997.
(i) This amendment becomes effective on November 20, 1998.
Issued in Renton, Washington, on October 6, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-27460 Filed 10-15-98; 8:45 am]
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