[Federal Register Volume 69, Number 26 (Monday, February 9, 2004)]
[Rules and Regulations]
[Pages 5922-5924]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-2582]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NM-118-AD; Amendment 39-13463; AD 2004-03-19]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A320-111, -211, and -231 
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 certain Airbus Model A320-111, -211, and -231 
series airplanes, that currently requires repetitive inspections for 
cracking in the transition and pick-up angles in the lower part of the 
center fuselage area, and corrective action if necessary. That AD also 
provides for an optional terminating modification for the repetitive 
inspection requirements. This amendment reduces the compliance time for 
the inspections for cracking of the same area. The actions specified by 
this AD are intended to detect and correct fatigue cracking in the 
transition and pick-up angles of the lower part of the center fuselage, 
which could result in reduced structural integrity of the wing-fuselage 
support and fuselage pressure vessel. This action is intended to 
address the identified unsafe condition.

DATES: Effective March 15, 2004.
    The incorporation by reference of certain publications, as listed 
in the regulations, is approved by the Director of the Federal Register 
as of March 15, 2004.
    The incorporation by reference of certain other publications, as 
listed in the regulations, was approved previously by the Director of 
the Federal Register as of July 14, 1998 (63 FR 31345, June 9, 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 98-12-18, 
amendment 39-10573 (63 FR 31345, June 9, 1998), which is applicable to 
certain Airbus Model A320-111, -211, and -231 series airplanes, was 
published in the Federal Register on November 18, 2003 (68 FR 65008). 
The action proposed to continue to require repetitive inspections for 
cracking in the transition and pick-up angles in the lower part of the 
center fuselage area, and corrective action if necessary. The action 
also provides for an optional terminating modification for the 
repetitive inspection requirements. The new action proposed to reduce 
the compliance time for the inspections for cracking of the same area.

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

    There are approximately 24 airplanes of U.S. registry that will be 
affected by this AD. The new requirements of this AD add no additional 
economic burden. The current costs for this AD are repeated for the 
convenience of affected operators, as follows:
    The inspections that are currently required by AD 98-12-18, and 
retained in this AD, take about 9 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 currently required actions on 
U.S. operators is estimated to be $14,040, or $585 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. 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 incidental costs, such as the time required to 
gain access and close up, planning time, or time necessitated by other 
administrative actions.
    If an operator chooses to do the optional terminating modification 
rather than continue the repetitive inspections, it will take between 5 
and 10 work hours per airplane to accomplish the modification, at an 
average labor rate of $65 per work hour. Required parts will cost 
between $1,077 and $1,837 per airplane. Based on these figures, the 
cost impact of the modification is estimated to be between $1,402 and 
$2,487 per airplane.

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,

[[Page 5923]]

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 39-10573 (63 FR 
31345, June 9, 1998), and by adding a new airworthiness directive (AD), 
amendment 39-13463, to read as follows:

2004-03-19 Airbus: Amendment 39-13463. Docket 2002-NM-118-AD. 
Supersedes AD 98-12-18, Amendment 39-10573.

    Applicability: Model A320-111, -211, and -231 series airplanes; 
certificated in any category; as listed in Airbus Service Bulletin 
A320-53-1027, Revision 03, dated February 12, 2002; or Airbus 
Service Bulletin A320-53-1028, Revision 01, dated February 12, 2002.
    Compliance: Required as indicated, unless accomplished 
previously.
    To detect and correct fatigue cracking in the transition and 
pick-up angles of the lower part of the center fuselage, which could 
result in reduced structural integrity of the wing-fuselage support 
and fuselage pressure vessel, accomplish the following:

Restatement of Requirements of AD 98-12-18

Repetitive Inspections/Corrective Actions/Modification

    (a) Prior to the accumulation of 16,000 total landings, or 
within 6 months after July 14, 1998 (the effective date of AD 98-12-
18, amendment 39-10573), whichever occurs later, accomplish 
paragraphs (a)(1) and (a)(2) of this AD, in accordance with Airbus 
Service Bulletin A320-53-1028, dated March 1, 1994.
    (1) Perform a detailed inspection to detect cracks of the 
transition angle, in accordance with the service bulletin.
    (i) If no crack is detected during the detailed inspection 
required by paragraph (a)(1) of this AD, accomplish either paragraph 
(a)(1)(i)(A) or paragraph (a)(1)(i)(B) of this AD.
    (A) Repeat the detailed inspection thereafter at intervals not 
to exceed 12,000 landings. Or
    (B) Prior to further flight, modify the center fuselage in 
accordance with Airbus Service Bulletin A320-53-1027, Revision 2, 
dated June 8, 1995. Accomplishment of the modification constitutes 
terminating action for the repetitive inspection requirements of 
paragraph (a)(1)(i)(A) of this AD.
    (ii) If any crack is detected during the detailed inspection 
required by paragraph (a)(1) of this AD, prior to further flight, 
replace the transition angle with a new transition angle, in 
accordance with Airbus Service Bulletin A320-53-1027, Revision 2, 
dated June 8, 1995.
    (2) Perform a rotating probe inspection to detect cracks of the 
pick-up angle, in accordance with the service bulletin.
    (i) If no crack is detected during the rotating probe inspection 
required by paragraph (a)(2) of this AD, accomplish either paragraph 
(a)(2)(i)(A) or (a)(2)(i)(B) of this AD.
    (A) Repeat the rotating probe inspection thereafter at intervals 
not to exceed 12,000 landings. Or
    (B) Prior to further flight, modify the center fuselage in 
accordance with Airbus Service Bulletin A320-53-1027, Revision 2, 
dated June 8, 1995. Accomplishment of the modification constitutes 
terminating action for the repetitive inspection requirements of 
paragraph (a)(2)(i)(A) of this AD.
    (ii) If any crack is detected and it is less than 1.9 mm in 
length, prior to further flight, accomplish the applicable 
corrective actions specified in the service bulletin. For holes that 
have not been modified in accordance with the service bulletin, 
repeat the rotating probe inspection thereafter at intervals not to 
exceed 12,000 landings.
    (iii) If any crack is detected and it is 1.9 mm or greater in 
length, prior to further flight, repair it in accordance with a 
method approved by the Manager, International Branch, ANM-116, FAA, 
Transport Airplane Directorate.

    Note 1: Accomplishment of the replacement/modification in 
accordance with Airbus Service Bulletin A320-53-1027, dated March 1, 
1994; or Revision 1, dated September 5, 1994, prior to the effective 
date of this AD, is considered acceptable for compliance with the 
applicable action specified in this AD.

New Requirements of This AD

Detailed and Rotating Probe Inspections

    (b) For airplanes on which the modification specified in AD 98-
12-18 has not been done: Do the applicable inspections specified in 
paragraphs (b)(1) and (b)(2) of this AD, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A320-53-1028, 
Revision 01, dated February 12, 2002.
    (1) For airplanes on which the inspections required by AD 98-12-
18 have been done: Within 12,000 flight cycles after accomplishment 
of the last inspection required by paragraphs (a)(1)(i)(A) and 
(a)(2)(i)(A) of this AD, as applicable; do a detailed inspection of 
the transition angle and a rotating probe inspection of the pick-up 
angle in the lower part of the center fuselage area for cracking.
    (2) For airplanes on which the inspections required by AD 98-12-
18 have not been done: At the later of the times specified in 
paragraph (b)(2)(i) or (b)(2)(ii) of this AD; do a detailed 
inspection of the transition angle and a rotating probe inspection 
of the pick-up angle in the lower part of the center fuselage area 
for cracking.
    (i) Before the accumulation of 10,400 total flight cycles, or 
24,600 total flight hours, whichever is first.
    (ii) Before the accumulation of 16,000 total flight cycles, or 
within 3,500 flight cycles after the effective date of this AD, 
whichever is first.

Repetitive Inspections

    (c) Repeat the detailed and rotating probe inspections specified 
in paragraphs (b)(1) and (b)(2) of this AD at intervals not to 
exceed 10,400 flight cycles or 24,600 flight hours, whichever is 
first, until the modification specified in paragraph (e) of this AD 
has been done.

    Note 2: For the purposes of this AD, a detailed inspection is 
defined as: ``An intensive visual examination of a specific 
structural area, system, installation, or assembly to detect damage, 
failure, or irregularity. Available lighting is normally 
supplemented with a direct source of good lighting at intensity 
deemed appropriate by the inspector. Inspection aids such as mirror, 
magnifying lenses, etc., may be used. Surface cleaning and elaborate 
access procedures may be required.''

Corrective Action

    (d) If any cracking is found during any inspection required by 
paragraph (b) or (c) of this AD: Prior to further flight, either 
repair the cracking per the Accomplishment Instructions of Airbus 
Service Bulletin A320-53-1028, Revision 01, dated February 12, 2002; 
or do the modification specified in paragraph (e) of this AD. Where 
the service bulletin specifies to contact the manufacturer for 
repair instructions, prior to further flight, repair the cracking in 
accordance with a method approved by the Manager, International 
Branch, ANM-116; or the Direction Generale de l'Aviation Civile (or 
its

[[Page 5924]]

delegated agent). If the cracking is repaired, repeat the 
inspections as required by paragraph (c) of this AD.

Modification

    (e) Modification of the transition and pick-up angles in the 
lower part of the center fuselage in accordance with paragraphs 3.A. 
through 3.D. of the Accomplishment Instructions of Airbus Service 
Bulletin A320-53-1027, Revision 03, dated February 12, 2002, ends 
the repetitive inspections required by this AD.

Alternative Methods of Compliance

    (f) 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

    (g) Unless otherwise specified in this AD, the actions shall be 
done in accordance with Airbus Service Bulletin A320-53-1027, 
Revision 2, dated June 8, 1995; Airbus Service Bulletin A320-53-
1027, Revision 03, dated February 12, 2002; Airbus Service Bulletin 
A320-53-1028, dated March 1, 1994; and Airbus Service Bulletin A320-
53-1028, Revision 01, dated February 12, 2002; as applicable.
    (1) The incorporation by reference of Airbus Service Bulletin 
A320-53-1027, Revision 03, dated February 12, 2002; and Airbus 
Service Bulletin A320-53-1028, Revision 01, dated February 12, 2002; 
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 
A320-53-1027, Revision 2, dated June 8, 1995; and Airbus Service 
Bulletin A320-53-1028, dated March 1, 1994; was approved previously 
by the Director of the Federal Register as of July 14, 1998 (63 FR 
31345, June 9, 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 3: The subject of this AD is addressed in French 
airworthiness directive 2002-183(B), dated April 3, 2002.

Effective Date

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

    Issued in Renton, Washington, on January 30, 2004.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 04-2582 Filed 2-6-04; 8:45 am]
BILLING CODE 4910-13-P