Airworthiness Directives; Airbus Model A310 Series Airplanes

[Federal Register Volume 64, Number 183 (Wednesday, September 22, 1999)]
[Rules and Regulations]
[Pages 51193-51195]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-24199]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-91-AD; Amendment 39-11325; AD 99-19-38]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A310 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 A310 series airplanes, that requires 
repetitive high frequency eddy current inspections to detect fatigue 
cracking at the hole in the lower web of the inner and outer attachment 
fittings of the number 3 wing spoilers; and corrective actions, if 
necessary. This amendment also provides for an optional modification, 
which terminates the repetitive inspections. 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 fatigue cracking and eventual 
failure of the attachment fittings of the number 3 wing spoilers.

DATES: Effective October 27, 1999.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of October 27, 1999.

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 A310 series 
airplanes was

[[Page 51194]]

published in the Federal Register on July 23, 1999 (64 FR 39946). That 
action proposed to require repetitive high frequency eddy current 
inspections to detect fatigue cracking at the hole in the lower web of 
the inner and outer attachment fittings of the number 3 wing spoilers; 
and corrective actions, if necessary. That action also provides for an 
optional modification, which would terminate the repetitive 
inspections.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were submitted in response 
to the proposal or the FAA's determination of the cost to the public.

Conclusion

    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 44 airplanes of U.S. registry will be 
affected by this AD, that it will take approximately 2 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 required AD on U.S. operators is estimated to be $5,280, 
or $120 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.
    Should an operator elect to accomplish the optional terminating 
action rather than continue the repetitive inspections, it would take 
approximately 110 work hours per airplane to accomplish the 
modification, at an average labor rate of $60 per work hour. Required 
parts will cost approximately $13,280 per airplane. Based on these 
figures, the cost impact of this optional terminating action is 
estimated to be $19,880 per airplane.

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:

99-19-38  Airbus Industrie: Amendment 39-11325. Docket 99-NM-91-AD.

    Applicability: Model A310 series airplanes, on which Airbus 
Industrie Modification 04117 or 04799 has been installed in 
production; except those airplanes on which Airbus Industrie 
Modification 11929 (reference Airbus Industrie Service Bulletin 
A310-57-2079, dated July 21, 1998, or Revision 01, dated January 11, 
1999) has 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 detect and correct fatigue cracking and eventual failure of 
the attachment fittings of the number 3 wing spoilers, which, if 
left undetected, could lead to fuel leaks and loss of various 
hydraulic and electrical systems, accomplish the following:

Inspection

    (a) At the applicable compliance time specified in paragraph 
(a)(1), (a)(2), or (a)(3) of this AD, perform a high frequency eddy 
current inspection to detect fatigue cracking at the hole in the 
lower web of the inner and outer attachment fittings of the number 3 
wing spoilers, in accordance with Airbus Industrie Service Bulletin 
A310-57-2078, Revision 01, dated January 11, 1999. Repeat the 
inspection thereafter at intervals not to exceed 1,200 flight 
cycles.
    (1) For airplanes that have accumulated 14,200 or fewer total 
flight cycles as of the effective date of this AD, accomplish the 
inspection required by paragraph (a) of this AD prior to the 
accumulation 10,800 total flight cycles or within 800 flight cycles 
after the effective date of this AD, whichever occurs later.
    (2) For airplanes that have accumulated more than 14,200 total 
flight cycles but fewer than 15,400 total flight cycles as of the 
effective date of this AD, accomplish the inspection required by 
paragraph (a) of this AD within 400 flight cycles after the 
effective date of this AD.
    (3) For airplanes that have accumulated 15,400 or more total 
flight cycles as of the effective date of this AD, accomplish the 
inspection required by paragraph (a) of this AD within 200 flight 
cycles after the effective date of this AD.

    Note 2: Inspection of the attachment fittings of the number 3 
wing spoilers accomplished prior to the effective date of this AD in 
accordance with the original issue of Airbus Industrie Service 
Bulletin A310-57-2078, dated July 21, 1998, is considered acceptable 
for compliance with the inspection required by paragraph (a) of this 
AD.

Replacement

    (b) If any crack is found during any inspection required by 
paragraph (a) of this AD, at the applicable compliance time 
specified in paragraph (b)(1), (b)(2), or (b)(3) of this AD, perform 
a high frequency eddy current inspection for fatigue cracking of the 
holes in the wing structure; ream and cold work those holes; and 
replace the cracked aluminum wing spoiler number 3 actuator 
attachment fitting with a new steel fitting; in accordance with 
Airbus Industrie Service Bulletin A310-57-2079, Revision 01, dated 
January 11, 1999. Accomplishment of the replacement constitutes 
terminating action for the repetitive inspection requirements of 
paragraph (a) of this AD for the replaced fitting.
    (1) If the crack is less than 0.078 inches (2.0 mm) in length, 
inspect, ream, cold work, and replace within 100 flight cycles after 
accomplishment of the inspection.
    (2) If the crack is 0.078 inches (2.0 mm) in length or greater 
and less than 0.118 inches (5.0 mm) in length, inspect, ream, cold 
work, and replace within 50 flight cycles after accomplishment of 
the inspection.

[[Page 51195]]

    (3) If the crack is greater than 0.118 inches (5.0 mm) in 
length, inspect, ream, cold work, and replace prior to further 
flight.

Optional Terminating Modification

    (c) Accomplishment of the high frequency eddy current inspection 
for fatigue cracking of the holes in the wing structure; reaming and 
cold working of those holes; and replacement of all aluminum wing 
spoiler number 3 actuator attachment fittings with new steel 
fittings; in accordance with Airbus Industrie Service Bulletin A310-
57-2079, Revision 01, dated January 11, 1999; constitutes 
terminating action for the repetitive inspection requirements of 
paragraph (a) of this AD.

    Note 3: Replacement of aluminum attachment fittings of the 
number 3 wing spoilers with steel fittings accomplished prior to the 
effective date of this AD in accordance with the original issue of 
Airbus Industrie Service Bulletin A310-57-2079, dated July 21, 1998, 
is considered acceptable for compliance with the applicable fitting 
replacement specified in paragraphs (b) and (c) of this AD.

Wing Repair

    (d) If any crack is found in the wing structure during any 
inspection required by paragraph (b) or specified in paragraph (c) 
of this AD, prior to further flight, repair in accordance with a 
method approved by either the Manager, International Branch, ANM-
116, FAA, Transport Airplane Directorate; or the Direction Generale 
de l'Aviation Civile (DGAC) (or its delegated agent). For a repair 
method to be approved by the Manager, International Branch, ANM-116, 
as required by this paragraph, the Manager's approval letter must 
specifically reference this AD.

    Note 4: For paragraph (d) of this AD, the wing spoiler number 3 
actuator attachment fittings are not considered part of the wing 
structure.

Alternative Methods of Compliance

    (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, 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 5: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the International Branch, ANM-116.

Special Flight Permits

    (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.

Incorporation by Reference

    (g) Except as provided by paragraph (d) of this AD, the actions 
shall be done in accordance with Airbus Industrie Service Bulletin 
A310-57-2078, Revision 01, dated January 11, 1999; or Airbus 
Industrie Service Bulletin A310-57-2079, Revision 01, dated January 
11, 1999; 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 6: The subject of this AD is addressed in French 
airworthiness directive 98-483-271(B) R1, dated June 2, 1999.

    (h) This amendment becomes effective on October 27, 1999.

    Issued in Renton, Washington, on September 10, 1999.
D.L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 99-24199 Filed 9-21-99; 8:45 am]
BILLING CODE 4910-13-P

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