[Federal Register Volume 69, Number 63 (Thursday, April 1, 2004)]
[Proposed Rules]
[Pages 17103-17105]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-7296]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-NM-187-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A319 and A320 Series 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the adoption of a new airworthiness 
directive (AD) that is applicable to certain Airbus Model A319 and A320 
series airplanes. This proposal would require repetitive detailed 
inspections to detect cracks in the keel beam side panels, and repair 
if necessary. Accomplishment of the repair ends the repetitive 
inspections for that repaired area. This action is necessary to detect 
and correct fatigue cracks on the side panels of the keel beams, which 
could result in reduced structural integrity of the airplane. This 
action is intended to address the identified unsafe condition.

DATES: Comments must be received by May 3, 2004.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2003-NM-187-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. 2003-NM-187-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 Ronda Point Maurice Ballonet, 31707 Blanca 
Codex, France. This information may be examined at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington.

FOR FURTHER INFORMATION CONTACT: Tim Dulin, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2141; 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:


[[Page 17104]]


     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 2003-NM-187-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. 2003-NM-187-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    The DGAC, which is the airworthiness authority for France, notified 
the FAA that an unsafe condition may exist on certain Airbus Model A319 
and A320 series airplanes. The DGAC advises that, during certification 
structural fatigue tests, cracks were found on the side panels of the 
keel beams. Such fatigue cracking, if not detected and corrected in a 
timely manner, could result in reduced structural integrity of the 
fuselage.

Explanation of Relevant Service Information

    Airbus has issued Service Bulletin A320-53-1060, dated June 19, 
2002, which describes procedures for repetitive detailed inspections to 
detect cracks in the keel beam side panels, and repair if necessary. 
Accomplishment of the repair ends the repetitive inspections for that 
repaired area. Accomplishment of the actions specified in the service 
bulletin is intended to adequately address the identified unsafe 
condition. The DGAC classified this service bulletin as mandatory and 
issued French airworthiness directive 2003-146(B), dated April 16, 2003 
(a correction was issued May 14, 2003), in order to assure 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 
section 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 require accomplishment of 
the actions specified in the service bulletin described previously, 
except as discussed below.

Differences Between Proposed AD and Service Bulletin

    Operators should note that, although the service bulletin specifies 
that the manufacturer may be contacted for disposition of certain 
repair conditions, this proposed AD would require the repair of those 
conditions to be accomplished per a method approved by either the FAA, 
or the Direction Generale De L'Aviation Civile (DGAC), France (or its 
delegated agent). In light of the type of repair that would be required 
to address the identified unsafe condition, and in consonance with 
existing bilateral airworthiness agreements, the FAA has determined 
that, for this proposed AD, a repair approved by either the FAA or the 
DGAC (or its delegated agent) would be acceptable for compliance with 
this proposed AD.
    Operators should also note that, unlike the procedures described in 
the service bulletin, this proposed AD would not permit further flight 
if cracks are detected in the keel beam side panel. The FAA has 
determined that, because of the safety implications and consequences 
associated with such cracking, any subject keel beam side panel that is 
found to be cracked must be repaired or modified before further flight.

Cost Impact

    The FAA estimates that 400 Model A319 and A320 series airplanes of 
U.S. registry would be affected by this proposed AD, that it would take 
approximately 13 work hours per airplane to accomplish the proposed 
inspection, and that the average labor rate is $65 per work hour. Based 
on these figures, the cost impact of the proposed AD on U.S. operators 
is estimated to be $338,000, or $845 per airplane, per inspection 
cycle.
    The cost impact figure discussed above is based on assumptions that 
no operator has yet accomplished any of 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.

[[Page 17105]]

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 adding the following new 
airworthiness directive:

Airbus: Docket 2003-NM-187-AD.

    Applicability: Model A319 and A320 series airplanes, 
certificated in any category; except those airplanes on which Airbus 
Modification 30355 has been incorporated in production.
    Compliance: Required as indicated, unless accomplished 
previously.
    To detect and correct fatigue cracks on the side panels of the 
keel beams, which could result in reduced structural integrity of 
the airplane, accomplish the following:

Service Bulletin

    (a) The term ``service bulletin,'' as used in this AD, means the 
Accomplishment Instructions of Airbus Service Bulletin A320-53-1060, 
dated June 19, 2002.

Initial Inspection

    (b) Perform a detailed inspection to detect cracks in the keel 
beam side panels, in accordance with the service bulletin, at the 
time specified in either paragraph (b)(1) or (b)(2) of this AD, as 
applicable.

    Note 1: 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 a 
mirror, magnifying lenses, etc., may be used. Surface cleaning and 
elaborate access procedures may be required.''

    (1) For airplanes that have not been inspected per Maintenance 
Review Board (MRB) task 53-31-42: Inspect at the later of the times 
specified in paragraph (b)(1)(i) and (b)(1)(ii) of this AD.
    (i) Prior to the accumulation of 24,200 total flight cycles, or 
48,400 total flight hours, whichever occurs first.
    (ii) Within 3,500 flight cycles after the effective date of this 
AD.
    (2) For airplanes that have been inspected per MRB task 53-31-
42: Inspect at the later of the times specified in paragraph 
(b)(2)(i) and (b)(2)(ii) of this AD.
    (i) Within 4,300 flight cycles or 9,600 flight hours after the 
last inspection per MRB task 53-31-42, whichever occurs first.
    (ii) Within 3,500 flight cycles after the effective date of this 
AD.

Repetitive Inspections

    (c) Repeat the detailed inspection required by paragraph (b) of 
this AD at intervals not to exceed 4,300 flight cycles or 9,600 
flight hours, whichever occurs first.

Corrective Actions

    (d) If any crack is found in ``Area A'' during any inspection 
required by this AD, before further flight, repair the affected area 
in accordance with the service bulletin. Once a repair has been 
accomplished to ``Area A,'' the repetitive inspections of ``Area A'' 
required by paragraphs (b) and (c) of this AD are no longer required 
for that side of the keel beam.
    (e) If any crack is found in ``Area B'' during any inspection 
required by this AD, before further flight, repair the affected 
structure per 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).

Alternative Methods of Compliance

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

    Note 2: The subject of this AD is addressed in French 
airworthiness directive 2003-146(B), dated April 16, 2003 (a 
correction was issued May 14, 2003).



    Issued in Renton, Washington, on March 24, 2004.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 04-7296 Filed 3-31-04; 8:45 am]
BILLING CODE 4910-13-P