[Federal Register Volume 69, Number 30 (Friday, February 13, 2004)]
[Proposed Rules]
[Pages 7176-7179]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-3207]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-254-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A320 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: This document proposes the supersedure of an existing 
airworthiness directive (AD), applicable to certain Airbus Model A320 
series airplanes, that currently requires modification of the rear spar 
web of the wing, cold expansion of certain attachment holes for the 
forward pintle fitting and certain holes at the actuating cylinder 
anchorage of the main landing gear (MLG), repetitive inspections for 
fatigue cracking in certain areas of the rear spar of the wing, and 
corrective action if necessary. That AD also provides for optional 
terminating action for the requirements of the AD. This proposed AD 
would revise the threshold and repetitive intervals for the inspection. 
The actions specified by the proposed AD are intended to detect and 
correct fatigue cracking, which may lead to reduced structural 
integrity of the wing and the MLG. This action is intended to address 
the identified unsafe condition.

[[Page 7177]]


DATES: Comments must be received by March 15, 2004.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2001-NM-254-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9 a.m. and 3 p.m., Monday through Friday, except 
Federal holidays. Comments may be submitted via fax to (425) 227-1232. 
Comments may also be sent via the Internet using the following address: 
[email protected]. Comments sent via fax or the Internet must 
contain ``Docket No. 2001-NM-254-AD'' in the subject line and need not 
be submitted in triplicate. Comments sent via the Internet as attached 
electronic files must be formatted in Microsoft Word 97 or 2000 or 
ASCII text.
    The service information referenced in the proposed rule may be 
obtained from Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac 
Cedex, France. This information may be examined at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington.

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:

Comments Invited

    Interested persons are invited to participate in the making of the 
proposed rule by submitting such written data, views, or arguments as 
they may desire. Communications shall identify the Rules Docket number 
and be submitted in triplicate to the address specified above. All 
communications received on or before the closing date for comments, 
specified above, will be considered before taking action on the 
proposed rule. The proposals contained in this action may be changed in 
light of the comments received.
    Submit comments using the following format:
     Organize comments issue-by-issue. For example, 
discuss a request to change the compliance time and a request to change 
the service bulletin reference as two separate issues.
     For each issue, state what specific change to 
the proposed AD is being requested.
     Include justification (e.g., reasons or data) 
for each request.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the proposed rule. All 
comments submitted will be available, both before and after the closing 
date for comments, in the Rules Docket for examination by interested 
persons. A report summarizing each FAA-public contact concerned with 
the substance of this proposal will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this action must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2001-NM-254-AD.'' The postcard will be date stamped 
and returned to the commenter.

Availability of NPRMs

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, Transport Airplane Directorate, ANM-114, Attention: Rules 
Docket No. 2001-NM-254-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    On May 16, 2000, the FAA issued AD 2000-10-15, amendment 39-11739 
(65 FR 34069, May 26, 2000), applicable to certain Airbus Model A320 
series airplanes, to require modification of the rear spar web of the 
wing, cold expansion of certain attachment holes for the forward pintle 
fitting and certain holes at the actuating cylinder anchorage of the 
main landing gear (MLG), repetitive inspections for fatigue cracking of 
certain areas of the rear spar of the wing, and corrective action if 
necessary. That AD also provides for optional terminating action for 
the requirements of the AD. That action was prompted by the results of 
fatigue testing conducted by the manufacturer.
    The requirements of AD 2000-10-15 are intended to detect and 
correct fatigue cracking in certain areas of the rear spar of the wing, 
which may lead to reduced structural integrity of the wing and the MLG.

Actions Since Issuance of Previous Rule

    Since we issued AD 2000-10-15, the manufacturer discovered the 
potential for additional cracking on an airplane that had been modified 
in accordance with that AD. This finding has led to an adjustment of 
the related ``reference fatigue mission'' for Model A320 series 
airplanes, and resulted in revised inspection thresholds and repetitive 
intervals expressed in both flight cycles and flight hours.

Explanation of Relevant Service Information

    AD 2000-10-15 cites Airbus Service Bulletins A320-57-1088, Revision 
02, and A320-57-1089, Revision 02 and earlier, as the appropriate 
sources of service information for the inspections and optional 
modification, respectively. Airbus has since issued Service Bulletins 
A320-57-1088, Revision 04, dated August 16, 2001; and A320-57-1089, 
Revision 03, dated February 9, 2001. Service Bulletin A320-57-1088 
revised the compliance times to incorporate flight hours in addition to 
flight cycles; otherwise the new revisions describe essentially the 
same procedures as those described in the earlier versions. The 
Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC), which is 
the airworthiness authority for France, mandated Service Bulletin A310-
57-1088 and approved Service Bulletin A320-57-1089. The DGAC issued 
French airworthiness directive 2001-249(B), dated June 27, 2001, to 
ensure the continued airworthiness of these airplanes in France.

FAA's Conclusions

    This airplane model is manufactured in France and is type 
certificated for operation in the United States under the provisions of 
Sec. 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the 
applicable bilateral airworthiness agreement. Pursuant to this 
bilateral airworthiness agreement, the DGAC has kept the FAA informed 
of the situation described above. The FAA has examined the findings of 
the DGAC, reviewed all available information, and determined that AD 
action is necessary for products of this type design that are 
certificated for operation in the United States.

Explanation of Requirements of Proposed Rule

    Since an unsafe condition has been identified that is likely to 
exist or develop on other airplanes of the same type design registered 
in the United States, the proposed AD would supersede AD 2000-10-15 to 
continue to require modification of the rear spar web of the wing, cold 
expansion of certain attachment holes for the forward pintle fitting 
and certain holes at the actuating cylinder anchorage of the MLG, 
repetitive inspections for fatigue cracking in certain areas of the 
rear spar of the wing, and corrective action if necessary. The proposed 
AD would also continue to provide for optional terminating action. This 
proposed AD would revise the thresholds and repetitive intervals for 
the inspection.

[[Page 7178]]

The proposed compliance times for the initial inspection range from 
12,000 to 17,300 total flight cycles; or from 22,400 to 37,300 total 
flight hours. The actions would be required to be accomplished in 
accordance with the service information described previously.

Cost Impact

    This proposed AD would affect about 126 airplanes of U.S. registry. 
The following table provides the cost estimates of the actions 
currently required by AD 2000-10-15:

Cost Estimates

--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                      Hourly labor
                Action                   Work hours       rate               Parts cost                             Cost per airplane
--------------------------------------------------------------------------------------------------------------------------------------------------------
Modification..........................           60             $65  $0.......................  $3,900.
Cold expansion........................          600              65  $0.......................  $39,000.
Inspection............................           24              65  $0.......................  $1,560, per inspection cycle.
Optional terminating action...........          750              65  $27,036-$32,727            $75,786-$81,477.
                                                                      (depending on action
                                                                      airplane configuration).
--------------------------------------------------------------------------------------------------------------------------------------------------------

    This proposed AD would not add any new actions and therefore would 
not increase the economic burden on operators--except for the 
additional cost associated with a potentially shortened inspection 
interval.
    The cost impact figures discussed above are based on assumptions 
that no operator has yet accomplished the proposed 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.

Regulatory Impact

    The regulations proposed herein would 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 proposal would not have federalism implications 
under Executive Order 13132.
    For the reasons discussed above, I certify that this proposed 
regulation (1) is not a ``significant regulatory action'' under 
Executive Order 12866; (2) is not a ``significant rule'' under the DOT 
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 
and (3) if promulgated, 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 copy of the draft 
regulatory evaluation prepared for this action is contained in the 
Rules Docket. A copy of it may be obtained by contacting the Rules 
Docket at the location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 
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 removing amendment 39-11739 (65 FR 
34069, May 26, 2000), and by adding a new airworthiness directive (AD), 
to read as follows:

Airbus: Docket 2001-NM-254-AD. Supersedes AD 2000-10-15, Amendment 
39-11739.

    Applicability: Model A320 series airplanes, certificated in any 
category, except those modified in accordance with Airbus 
Modification 24591 (Airbus Service Bulletin A320-57-1089, dated 
December 22, 1996; Revision 01, dated April 17, 1997; or Revision 
02, dated November 6, 1998; or Revision 03, dated February 9, 2001).
    Compliance: Required as indicated, unless accomplished 
previously.
    To detect and correct fatigue cracking in certain areas of the 
rear spar of the wing, which may lead to reduced structural 
integrity of the wing and the main landing gear (MLG), accomplish 
the following:

Restatement of Certain Requirements of AD 2000-10-15

Modification

    (a) For airplanes having manufacturer's serial numbers (MSN) 003 
through 008 inclusive, and 010 through 021 inclusive: Prior to the 
accumulation of 12,000 total flight cycles, or within 500 flight 
cycles after June 11, 1993 (the effective date of AD 93-08-15, 
amendment 39-8563), whichever occurs later, modify the inner rear 
spar web of the wing in accordance with Airbus Service Bulletin 
A320-57-1004, Revision 1, dated September 24, 1992, or Revision 2, 
dated June 14, 1993.
    (b) For airplanes having MSNs 002 through 051 inclusive: Prior 
to the accumulation of 12,000 total flight cycles, or within 2,000 
flight cycles after February 14, 1994 (the effective date of AD 93-
25-13, amendment 39-8777), whichever occurs later, accomplish the 
requirements of paragraphs (b)(1) and (b)(2) of this AD in 
accordance with Airbus Service Bulletin A320-57-1060, dated December 
8, 1992; or Revision 2, dated December 16, 1994.
    (1) Perform a cold expansion of all the attachment holes for the 
forward pintle fitting of the MLG, except for the holes that are for 
taper-lok bolts.
    (2) Perform a cold expansion of the holes at the actuating 
cylinder anchorage of the MLG.

    Note 1: Accomplishment of the cold expansion in accordance with 
Airbus Service Bulletin A320-57-1060, Revision 1, dated April 26, 
1993, is also acceptable for compliance with the requirements of 
paragraph (b) of this AD.

New Requirements of This AD

Ultrasonic Inspection

    (c) Do an ultrasonic inspection for cracking of the rear spar of 
the wing, in accordance with Airbus Service Bulletin A320-57-1088, 
Revision 04, dated August 6, 2001. Inspect at the applicable time 
specified in paragraph 1.E. of the service bulletin, except as 
required by paragraphs (c)(1) and (c)(2) of this AD.

    Note 2: An inspection done before the effective date of this AD 
in accordance with Airbus Service Bulletin A320-57-1088, Revision 
02, dated July 29, 1999; or Revision 03, dated February 9, 2001; is 
acceptable for compliance with the requirements of the initial 
inspection required by paragraph (c) of this AD.

    (1) For any airplane that has not been inspected but has 
exceeded the applicable specified compliance time as of the 
effective date of this AD: Inspect within 60 days after the 
effective date of this AD.
    (2) For any airplane that has been inspected before the 
effective date of this AD: Repeat the inspection within 3,600 flight 
cycles after the most recent inspection.

[[Page 7179]]

Repetitive Inspections

    (d) Repeat the inspection required by paragraph (c) of this AD 
at intervals not to exceed 3,600 flight cycles or 6,700 flight 
hours, whichever occurs first, until the requirements of paragraph 
(f) have been done.

Corrective Action

    (e) If any crack is found during any inspection required by 
paragraph (c) or (d) of this AD: Before 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).

Optional Terminating Action

    (f) Modification of all specified fastener holes in the rear 
spar of the wing terminates the initial and repetitive inspections 
required by paragraphs (c) and (d) of this AD, if the modification 
is done in accordance with Airbus Service Bulletin A320-57-1089, 
dated December 22, 1996; Revision 01, dated April 17, 1997; Revision 
02, dated November 6, 1998; or Revision 03, dated February 9, 2001. 
If done before the airplane accumulates 12,000 total flight cycles, 
the modification also terminates the actions required by paragraphs 
(a) and (b) of this AD.

Alternative Methods of Compliance

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

    Note 3: The subject of this AD is addressed in French 
airworthiness directive 2001-249(B), dated June 27, 2001.


    Issued in Renton, Washington, on February 5, 2004.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 04-3207 Filed 2-12-04; 8:45 am]
BILLING CODE 4910-13-P