[Federal Register Volume 68, Number 233 (Thursday, December 4, 2003)]
[Proposed Rules]
[Pages 67814-67816]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-30191]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NM-183-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 supersedure of 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 action 
would require repetitive ultrasonic inspections for fatigue cracking in 
the wing/fuselage joint cruciform fittings at a reduced inspection 
threshold and repetitive interval. This action also would add airplanes 
to the applicability of the existing AD. The actions specified by the 
proposed 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: Comments must be received by January 5, 2004.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2002-NM-183-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. 2002-NM-183-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 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:
    [sbull] 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.
    [sbull] For each issue, state what specific change to the proposed 
AD is being requested.
    [sbull] 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 2002-NM-183-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. 2002-NM-183-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    On February 13, 1998, the FAA issued AD 98-04-49, amendment 39-
10360 (63 FR 9934, February 27, 1998), applicable to all Airbus Model 
A320 series airplanes. That AD requires repetitive ultrasonic 
inspections to detect fatigue cracking in the wing/fuselage joint 
cruciform fittings, and corrective actions if necessary. That action 
was prompted by issuance of mandatory continuing airworthiness 
information by a foreign civil airworthiness authority. The 
requirements of that 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.

Actions Since Issuance of Previous Rule

    The inspection threshold and repetitive intervals specified in AD 
98-04-49 were based on full-scale fatigue tests. Since the issuance of 
that AD, the airplane manufacturer has surveyed the Model A320 series 
airplane fleet and found that parameters such as the weight of fuel at 
landing and the mean flight duration are higher than those defined for 
the analysis of fatigue-related tasks. Thus, the manufacturer has 
adjusted the reference fatigue mission. This adjustment has resulted in 
a reduction in the threshold and repetitive inspection intervals 
required by the existing AD. In addition, it has been determined that 
Model A319 series airplanes should also be subject to these same 
inspections at the reduced threshold and interval.

Explanation of Relevant Service Information

    Airbus has issued Service Bulletin A320-57-1051, Revision 04, dated 
November 27, 2001. (The existing AD refers to Revision 01 of that 
service bulletin, dated March 21, 1996, as the acceptable source of 
service information for the actions required by that AD.) Revision 04 
of the service bulletin describes procedures for repetitive ultrasonic 
inspections for cracking around fastener ``a'' on the rear section of 
the cruciform fitting at rib 1 on both wings. This inspection is 
similar to that described in Revision 01 of the service

[[Page 67815]]

bulletin. If a suspected crack is found, the service bulletin specifies 
to remove the fastener and perform a rotative probe inspection of the 
fastener hole. If no crack is found, the service bulletin specifies to 
install a new fastener of the same diameter as the one that was 
removed. If a crack is found that measures 2.5 mm or less, the service 
bulletin specifies to drill the hole to remove the crack, and perform a 
second rotative probe inspection of the drilled hole to detect any 
crack. If the crack has been removed, the service bulletin specifies to 
install bushings and a new bolt. If a crack is found that is more than 
2.5 mm, or if the second rotative probe inspection reveals that the 
crack is still present, the service bulletin specifies to contact the 
manufacturer for repair instructions. The Direction 
G[eacute]n[eacute]rale de l'Aviation Civile (DGAC), which is the 
airworthiness authority for France, classified this service bulletin as 
mandatory and issued French airworthiness directive 2002-340(B), dated 
June 26, 2002, to ensure the continued airworthiness of these airplanes 
in France.

FAA's Conclusions

    These airplane models are manufactured in France and are 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 supersede AD 98-04-49 to 
require repetitive ultrasonic inspections to detect fatigue cracking in 
the wing/fuselage joint cruciform fittings, and corrective actions if 
necessary. This action would require repetitive inspections on 
additional airplanes not included in the applicability of the existing 
AD. The actions would be required to be accomplished in accordance with 
the service bulletin described previously, except as discussed below.

Differences Between Proposed AD and Service Bulletin

    Although the service bulletin specifies that operators may contact 
the manufacturer for disposition of certain repair conditions, this 
proposal would require operators to repair those conditions per a 
method approved by either the FAA or the DGAC (or its delegated agent). 
In light of the type of repair that would be required to address the 
unsafe condition, and consistent with existing bilateral airworthiness 
agreements, we have determined that, for this proposed AD, a repair 
approved by either the FAA or the DGAC would be acceptable for 
compliance with this proposed AD.
    Operators also should note that, although the Accomplishment 
Instructions of the referenced service bulletin describe procedures for 
reporting inspection results to Airbus, this proposed AD would not 
require that action.

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 proposed AD would affect approximately 475 airplanes of 
U.S. registry. The new actions that are proposed in this AD action 
would 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 proposed 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 current or 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 39-10360 (63 FR 
9934, February 27, 1998), and by adding a new airworthiness directive 
(AD), to read as follows:

Airbus: 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

[[Page 67816]]

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.

    Note 1: The subject of this AD is addressed in French 
airworthiness directive 2002-340(B), dated June 26, 2002.


    Issued in Renton, Washington, on November 28, 2003.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 03-30191 Filed 12-3-03; 8:45 am]
BILLING CODE 4910-13-P