AD Amdt-39-10838

[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 [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 98-27460]


-----------------------------------------------------------------------

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.

-----------------------------------------------------------------------

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]
BILLING CODE 4910-13-U