[Federal Register Volume 69, Number 26 (Monday, February 9, 2004)]
[Rules and Regulations]
[Pages 5909-5911]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-2465]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NM-183-AD; Amendment 39-13450; AD 2004-03-06]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A319 and 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 all Airbus Model A320 series airplanes, that 
currently requires repetitive ultrasonic inspections to detect fatigue 
cracking in the wing/fuselage joint cruciform fittings, and corrective 
actions if necessary. This amendment requires repetitive ultrasonic 
inspections for fatigue cracking in the wing/fuselage joint cruciform 
fittings at a reduced inspection threshold and repetitive interval. 
This amendment also adds airplanes to the applicability. The actions 
specified by this AD are intended to detect and correct fatigue cracks 
on the wing/fuselage joint cruciform fittings, which could result in 
reduced structural integrity of the wing/fuselage. This action is 
intended to address the identified unsafe condition.

DATES: Effective March 15, 2004.
    The incorporation by reference of Airbus Service Bulletin A320-57-
1051, Revision 04, dated November 27, 2001, as listed in the 
regulations, is approved by the Director of the Federal Register as of 
March 15, 2004.
    The incorporation by reference of Airbus Service Bulletin A320-57-
1051, Revision 01, dated March 21, 1996, as listed in the regulations, 
was approved previously by the Director of the Federal Register as of 
April 3, 1998 (63 FR 9934, February 27, 1998).

ADDRESSES: The service information referenced in this AD may be 
obtained from Airbus, 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: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2125; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 98-04-49, 
amendment 39-10360 (63 FR 9934, February 27, 1998), which is applicable 
to all Airbus Model A320 series airplanes, was published in the Federal 
Register on December 4, 2003 (68 FR 67814). The action proposed to 
require repetitive ultrasonic inspections for fatigue cracking in the 
wing/fuselage joint cruciform fittings at an inspection threshold and 
repetitive interval reduced from those in the existing AD. The action 
also proposed to add airplanes to the applicability of the existing AD.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. The FAA received no comments in 
response to the proposal or our determination of the cost to the 
public.

Conclusion

    After careful review of the available data, we have determined that 
air safety and the public interest require the adoption of the rule as 
proposed.

Cost Impact

    The actions that are currently required by AD 98-04-49 are 
applicable to 132 airplanes of U.S. registry and take approximately 2 
work hours per airplane to accomplish (not including time for gaining 
access and closing up), at an average labor rate of $65 per work hour. 
Based on these figures, the cost impact of the currently required 
actions on U.S. operators is estimated to be $17,160, or $130 per 
airplane.
    This new AD affects approximately 475 airplanes of U.S. registry. 
The new actions that are required by this AD take approximately 2 work 
hours per airplane to accomplish, at an average labor rate of $65 per 
work hour. Based on these figures, the cost impact of the new 
requirements of this AD on U.S. operators is estimated to be $61,750, 
or $130 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. The cost impact figures discussed 
in AD rulemaking actions represent only the time necessary to perform 
the specific actions actually required by the AD. These figures 
typically do not include

[[Page 5910]]

incidental costs, such as the time required to gain access and close 
up, planning time, or time necessitated by other administrative 
actions.

Regulatory Impact

    The regulations adopted herein will not have a substantial direct 
effect 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, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    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

0
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

0
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]

0
2. Section 39.13 is amended by removing amendment 39-10360 (63 FR 9934, 
February 27, 1998), and by adding a new airworthiness directive (AD), 
amendment 39-13450, to read as follows:

2004-03-06 Airbus: Amendment 39-13450. Docket 2002-NM-183-AD. 
Supersedes AD 98-04-49, Amendment 39-10360.

    Applicability: All Model A319 and A320 series airplanes, 
certificated in any category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To detect and correct fatigue cracks on the wing/fuselage joint 
cruciform fittings, which could result in reduced structural 
integrity of the wing/fuselage, accomplish the following:

Requirements of AD 98-04-49

Ultrasonic Inspection (Model A320 Series Airplanes)

    (a) For Model A320 series airplanes: Prior to the accumulation 
of 28,000 total landings, or within 60 days after April 3, 1998 (the 
effective date of AD 98-04-49, amendment 39-10360), whichever occurs 
later, perform an ultrasonic inspection to detect fatigue cracking 
in the wing/fuselage joint cruciform fittings, in accordance with 
Airbus Service Bulletin A320-57-1051, Revision 01, dated March 21, 
1996.
    (1) If no cracking is detected, repeat the inspection thereafter 
at intervals not to exceed 20,000 landings, until paragraph (c) of 
this AD is accomplished.
    (2) If any crack is detected, prior to further flight, repair it 
in accordance with the service bulletin. Thereafter, repeat the 
inspection at the times specified in paragraph (a)(2)(i) or 
(a)(2)(ii) of this AD, as applicable.
    (i) If the crack that was detected and repaired was greater than 
2.5 mm: Repeat the inspection prior to the accumulation of 32,000 
landings since accomplishment of the repair; and thereafter at 
intervals not to exceed 32,000 landings.
    (ii) If the crack that was detected and repaired was less than 
or equal to 2.5 mm: Repeat the inspection prior to the accumulation 
of 28,000 landings since accomplishment of the repair; and 
thereafter at intervals not to exceed 20,000 landings.

New Requirements of This AD

Ultrasonic Inspection (Model A319 Series Airplanes)

    (b) For Model A319 series airplanes: Perform an ultrasonic 
inspection to detect fatigue cracking in the wing/fuselage joint 
cruciform fittings, in accordance with Airbus Service Bulletin A320-
57-1051, Revision 04, dated November 27, 2001. Do the initial 
inspection at the later of the times specified in paragraphs (b)(1) 
and (b)(2) of this AD. Repeat the inspection thereafter at intervals 
not to exceed the applicable interval specified in paragraph 1.E.(2) 
of the service bulletin.
    (1) Prior to the accumulation of 20,000 total flight cycles or 
42,000 total flight hours, whichever is first.
    (2) Prior to the accumulation of 28,000 total flight cycles or 
within 3,500 flight cycles after the effective date of this AD, 
whichever is first.

Ultrasonic Inspection (Model A320 Series Airplanes)

    (c) For Model A320 series airplanes: Perform an ultrasonic 
inspection to detect fatigue cracking in the wing/fuselage joint 
cruciform fittings, in accordance with Airbus Service Bulletin A320-
57-1051, Revision 04, dated November 27, 2001, at the later of the 
times specified in paragraphs (c)(1) and (c)(2) of this AD, except 
as required by paragraph (f) of this AD. Accomplishment of the 
inspection required by this paragraph terminates the repetitive 
inspections required by paragraph (a) of this AD. Except as required 
by paragraph (e) of this AD, repeat the ultrasonic inspection at 
intervals not to exceed the applicable interval specified in 
paragraph 1.E.(2) of the service bulletin.
    (1) Prior to the accumulation of 20,000 total flight cycles or 
42,000 total flight hours, whichever is first.
    (2) Prior to the accumulation of 28,000 total flight cycles or 
within 3,500 flight cycles after the effective date of this AD, 
whichever is first.

Cracking: Corrective Action and Repeat Inspections

    (d) If any crack is found during any inspection required by 
paragraph (b) or (c) of this AD: Before further flight, do all 
applicable actions in paragraphs B.(1)(b), C.(1), D., and E. 
(including removing the fastener, performing a rotative probe 
inspection to confirm the crack or determine the size of the crack, 
and accomplishing applicable corrective actions) of the 
Accomplishment Instructions of Airbus Service Bulletin A320-57-1051, 
Revision 04, dated November 27, 2001, except as provided by 
paragraph (e) of this AD.
    (e) If any crack is found during any inspection required by this 
AD, and the service bulletin recommends contacting Airbus for 
appropriate action: Before further flight, repair and perform 
repetitive inspections per a method and at a repetitive inspection 
interval approved by the Manager, International Branch, ANM-116, 
FAA, Transport Airplane Directorate; or the Direction 
G[eacute]n[eacute]rale de l'Aviation Civile (DGAC) (or its delegated 
agent).

Model A320 Series Airplanes Repaired Previously

    (f) For Model A320 series airplanes on which a crack measuring 
more than 2.5 mm was repaired prior to the effective date of this AD 
per Airbus Service Bulletin A320-57-1051, Revision 01, dated March 
21, 1996: Perform repetitive inspections per a method and at an 
interval approved by the Manager, International Branch, ANM-116, 
FAA, Transport Airplane Directorate; or the Direction 
G[eacute]n[eacute]rale de l'Aviation Civile (DGAC) (or its delegated 
agent).

Reporting of Inspection Results Not Required

    (g) Where the Accomplishment Instructions of Airbus Service 
Bulletin A320-57-1051, Revision 04, dated November 27, 2001, 
describe procedures for reporting inspection results to Airbus, this 
AD does not require such reporting.

Alternative Methods of Compliance

    (h) In accordance with 14 CFR 39.19, the Manager, International 
Branch, ANM-116, is authorized to approve alternative methods of 
compliance for this AD.

Incorporation by Reference

    (i) Unless otherwise provided by this AD, the actions shall be 
done in accordance with Airbus Service Bulletin A320-57-1051, 
Revision 01, dated March 21, 1996; and Airbus Service Bulletin A320-
57-1051, Revision 04, dated November 27, 2001; as applicable.
    (1) The incorporation by reference of Airbus Service Bulletin 
A320-57-1051,

[[Page 5911]]

Revision 04, dated November 27, 2001, is approved by the Director of 
the Federal Register, in accordance with 5 U.S.C. 552(a) and 1 CFR 
part 51.
    (2) The incorporation by reference of Airbus Service Bulletin 
A320-57-1051, Revision 01, dated March 21, 1996, was approved 
previously by the Director of the Federal Register as of April 3, 
1998 (63 FR 9934, February 27, 1998).
    (3) Copies may be obtained from Airbus, 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 1: The subject of this AD is addressed in French 
airworthiness directive 2002-340(B), dated June 26, 2002.

Effective Date

    (j) This amendment becomes effective on March 15, 2004.

    Issued in Renton, Washington, on January 29, 2004.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 04-2465 Filed 2-6-04; 8:45 am]
BILLING CODE 4910-13-P