[Federal Register Volume 63, Number 186 (Friday, September 25, 1998)]
[Rules and Regulations]
[Pages 51277-51279]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-25474]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-77-AD; Amendment 39-10798; AD 98-20-31]
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 adopts a new airworthiness directive (AD), 
applicable to certain Airbus Model A320 series airplanes, that requires 
repetitive inspections to detect cracking in the pressurized floor 
pick-up angles on the rear spar of the wing, and replacement of any 
cracked pick-up angle and its associated diaphragms with improved 
parts. Such replacement terminates the repetitive inspections for that 
angle. 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 
cracking in the pressurized floor pick-up angles at the rear spar of 
the wing, which could result in reduced structural integrity of the 
airframe.

DATES: Effective October 30, 1998.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of October 30, 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, 
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 A320 series 
airplanes was

[[Page 51278]]

published in the Federal Register on April 27, 1998 (63 FR 20546). That 
action proposed to require repetitive inspections to detect cracking in 
the pressurized floor pick-up angles on the rear spar of the wing, and 
replacement of any cracked pick-up angle and its associated diaphragms 
with improved parts. Such replacement would terminate the repetitive 
inspections for that angle.

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 Accept Additional Versions of Service Bulletins

    The commenter (the manufacturer) generally supports the proposed 
rule. However, the commenter states that an inspection performed in 
accordance with instructions defined in Airbus Service Bulletin A320-
57-1090, dated April 19, 1996, complies with the requirements of 
paragraph (a) of the proposed AD. (The proposed AD cited only Revision 
1 of that service bulletin as the appropriate means of compliance.)
    The commenter adds that accomplishment of the modification, in 
accordance with Airbus Service Bulletin A320-57-1025, Revision 2, dated 
November 25, 1994; Revision 3, dated May 22, 1995; or Revision 4, dated 
December 8, 1995; should be considered acceptable as terminating action 
for the proposed AD. (The proposed AD cited only Revision 5, dated June 
26, 1997, of that service bulletin as the appropriate means of 
compliance.)
    The FAA concurs that accomplishment of those earlier versions of 
the service bulletins, in lieu of the revision levels cited in the 
proposed rule, is acceptable for compliance with the requirements of 
this AD. The inspection procedures described in Airbus Service Bulletin 
A320-57-1090, dated April 19, 1996, are essentially the same as those 
described in Revision 1, dated June 10, 1997. Likewise, the 
modification procedures described in Airbus Service Bulletin A320-57-
1025, Revision 2, dated November 25, 1994; Revision 3, dated May 22, 
1995; and Revision 4, dated December 8, 1995; are essentially the same 
as those described in Revision 5, dated June 26, 1997. Therefore, the 
final rule has been revised to include Note 2 and Note 3, which credit 
operators for inspections and modifications accomplished prior to the 
effective date of the final rule in accordance with the referenced 
additional revision levels.

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 described 
previously. 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

    The FAA estimates that 120 airplanes of U.S. registry will be 
affected by this AD, that it will take approximately 8 work hours per 
airplane (including access and close) 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 inspection required by this AD 
on U.S. operators is estimated to be $57,600, or $480 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 that is provided by this AD, it would take approximately 140 
work hours to accomplish, at an average labor rate of $60 per work 
hour. The cost of required parts would be approximately $10,103 per 
airplane. Based on these figures, the cost impact of that optional 
terminating action would be $18,503 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:

98-20-31  Airbus Industrie: Amendment 39-10798. Docket 98-NM-77-AD.

    Applicability: Model A320 series airplanes, as listed in Airbus 
Service Bulletin A320-57-1090, Revision 01, dated June 10, 1997; 
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 (d) 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 cracking in the pressurized floor pick-up 
angles at the rear spar of the wing, which could result in reduced 
structural integrity of the airframe, accomplish the following:
    (a) Prior to the accumulation of 20,000 total flight cycles, or 
within 60 days after the effective date of this AD, whichever occurs 
later: Perform an eddy current inspection to detect cracking in the 
pressurized floor pick-up angles on the rear spar of the wing, in 
accordance with Airbus Service Bulletin A320-57-1090, Revision 01, 
dated June 10, 1997.


[[Page 51279]]


    Note 2: Accomplishment of the inspection prior to the effective 
date of this AD in accordance with Airbus Service Bulletin A320-57-
1090, dated April 19, 1996, is also considered acceptable for 
compliance with paragraph (a) of this AD.

    (1) If no cracking is found, repeat the inspection thereafter at 
intervals not to exceed 10,000 flight cycles.
    (2) If any cracking is found during any inspection required by 
this AD, prior to further flight, replace each cracked pick-up angle 
and its associated diaphragms with improved parts, in accordance 
with Airbus Service Bulletin A320-57-1025, Revision 05, dated June 
26, 1997. For all pick-up angles not replaced with improved angles, 
repeat the inspection thereafter at intervals not to exceed 10,000 
flight cycles.
    (b) Replacement of a pick-up angle and its associated diaphragms 
with improved parts, in accordance with Airbus Service Bulletin 
A320-57-1025, Revision 05, dated June 26, 1997, constitutes 
terminating action for the repetitive inspection requirements for 
that pick-up angle.

    Note 3: Accomplishment of the replacement prior to the effective 
date of this AD in accordance with Airbus Service Bulletin A320-57-
1025, Revision 2, dated November 25, 1994; Revision 3, dated May 22, 
1995; or Revision 4, dated December 8, 1995; is also considered 
acceptable for compliance with paragraphs (a)(2) and (b) of this AD.

    (c) If any crack is detected during any inspection required by 
this AD, and the applicable service bulletin specifies to contact 
Airbus for appropriate action: 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 (or its delegated 
agent).
    (d) 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 request through an appropriate FAA 
Principal Maintenance Inspector, who may add comments and then send 
it to the Manager, International Branch, ANM-116.

    Note 4: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the International Branch, ANM-116.

    (e) Special flight permits may be issued in accordance with 
Secs.  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.
    (f) The inspections shall be done in accordance with Airbus 
Service Bulletin A320-57-1090, Revision 01, dated June 10, 1997. 
Except as provided by paragraph (c) of this AD, the replacement, if 
accomplished, shall be done in accordance with Airbus Service 
Bulletin A320-57-1025, Revision 05, dated June 26, 1997, which 
contains the following effective pages:

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       Page number shown on page         Revision level shown on page              Date shown on page
----------------------------------------------------------------------------------------------------------------
1, 13, 30-32, 101, 102.................  05..........................  June 26, 1997.
2-5....................................  4...........................  December 8, 1995.
10, 15, 19, 24, 28, 29.................  3...........................  May 22, 1995.
6-9, 11, 12, 14, 16-18, 20-23 25-27, 33- 2...........................  November 25, 1994.
 100, 103-106.
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    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 5: The subject of this AD is addressed in French 
airworthiness directive CN 97-084-097 (B), dated March 12, 1997.

    (g) This amendment becomes effective on October 30, 1998.

    Issued in Renton, Washington, on September 17, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-25474 Filed 9-24-98; 8:45 am]
BILLING CODE 4910-13-P