[Federal Register Volume 65, Number 103 (Friday, May 26, 2000)]
[Rules and Regulations]
[Pages 34069-34072]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-12816]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-99-AD; Amendment 39-11739; AD 2000-10-15]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A320 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment supersedes two existing airworthiness 
directives (AD), applicable to certain Airbus Model A320 series 
airplanes, that currently require modification of the rear spar web of 
the wing and 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). This amendment adds a requirement for 
repetitive inspections to detect fatigue cracking in certain areas of 
the rear spar of the wing, and corrective action, if necessary. This

[[Page 34070]]

amendment also provides for optional terminating action for the 
requirements of this AD. This amendment is prompted by issuance of 
mandatory continuing airworthiness information by a foreign civil 
airworthiness authority. The actions specified by this AD are intended 
to detect and correct fatigue cracking, which may lead to reduced 
structural integrity of the wing and the MLG.

DATES: Effective June 30, 2000.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of June 30, 2000.
    The incorporation by reference of certain other publications was 
approved previously by the Director of the Federal Register as of June 
11, 1993 (58 FR 27923, May 12, 1993), and February 14, 1994 (59 FR 
1903, January 13, 1994).

ADDRESSES: The service information referenced in this AD may be 
obtained from Airbus Industrie, 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: Norman B. Martenson, Manager, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2110; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 93-08-15, 
amendment 39-8563 (58 FR 27923, May 12, 1993), and AD 93-25-13, 
amendment 39-8777 (59 FR 1903, January 13, 1994), which are both 
applicable to certain Airbus Model A320 series airplanes, was published 
in the Federal Register on February 10, 2000 (65 FR 6566). The action 
proposed to continue to require modification of the wing rear spar web 
and cold expansion of certain attachment holes for the forward pintle 
fitting and certain holes at the actuating cylinder anchorage of the 
MLG. The AD proposed to add a requirement for repetitive ultrasonic 
inspections to detect fatigue cracking in certain areas of the wing 
rear spar, and repair of cracking. The AD also proposed to provide for 
optional terminating action for the inspections proposed by this AD.

Comments Received

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.

Support for the Proposal

    One commenter concurs with the proposed AD. Another commenter 
states that Airbus Production Modification 24591 is installed on its 
airplanes; therefore, it is not affected by the proposed AD.

Inspection Threshold for Certain Airplanes

    One commenter requests that the proposed AD be revised to allow 
``Group 2'' airplanes to accomplish the initial inspection of the wing 
rear spar within 12,000 flight cycles after accomplishment of Airbus 
Service Bulletin A320-57-1060. The commenter defines ``Group 1'' 
airplanes as manufacturer's serial numbers (MSN) 002 through 021, on 
which Airbus Service Bulletins A320-57-1004 and A320-57-1060 are 
accomplished as retrofit. ``Group 2'' airplanes are defined as MSN's 
022 through 051, on which Airbus Modification 20740 (equivalent to 
A320-57-1004) has been accomplished in production, and Airbus Service 
Bulletin A320-57-1060 as retrofit.
    The commenter notes that ``Group 1'' airplanes are granted 12,000 
flight cycles after accomplishment of A320-57-1060, yet ``Group 2'' 
airplanes are required to undergo inspection prior to accumulation of 
17,300 total flight cycles, regardless of when modification per A320-
57-1060 was accomplished. The commenter states that ``Group 1'' and 
``Group 2'' airplanes are in the same configuration and will have a 
similar fatigue life; therefore, both should have the same inspection 
threshold.
    The FAA does not concur. Although the FAA acknowledges that ``Group 
1'' and ``Group 2'' airplanes may be in a similar modification 
configuration, the design configuration of these airplanes is 
different. ``Group 1'' airplanes are composed of Model A320-100 series 
airplanes, and ``Group 2'' airplanes are composed of Model A320-200 
series airplanes. Model A320-200 series airplanes are equipped with a 
center fuel tank (not installed on Model A320-100 series airplanes) 
that increases the airplanes' weight. For this reason, it is necessary 
that ``Group 2'' airplanes be inspected for cracking prior to 
accumulation of 17,300 total flight cycles, regardless of when Service 
Bulletin A320-57-1060 is accomplished. No change is made to the final 
rule.

Terminating Modification for Certain Airplanes

    One commenter requests that modification in accordance with Airbus 
Service Bulletin A320-57-1089 be considered as terminating action to 
all inspection requirements if accomplished prior to the initial 
inspection interval, or to repetitive inspections if accomplished after 
the initial inspection interval. The commenter states that terminating 
action credit is allowed under paragraph (e) of the proposed AD only if 
accomplished prior to 12,000 total flight cycles. The commenter states 
that accomplishment of the terminating modification includes a non-
destructive test inspection of the inner rear spar at each hole 
location. Since this inspection during the modification will ensure 
that the inner rear spar is free of defects, terminating action to the 
follow-on inspection requirements should also be provided.
    The FAA notes that terminating modification to the inspection 
requirements of the AD is already provided for in paragraph (e) of the 
proposed AD, and considers that clarification of the provisions for 
terminating modification is necessary. As stated in the second sentence 
of paragraph (e) of the AD, the threshold of 12,000 total flight cycles 
is required only if modification per Service Bulletin A320-57-1089 is 
chosen in lieu of accomplishing the modifications required by 
paragraphs (a) and (b) of the AD. However, the modification also 
constitutes acceptable terminating action for the ultrasonic inspection 
requirements of the AD, as stated in the first sentence of paragraph 
(e) of the AD. Paragraph (e) has been revised to more clearly specify 
the terminating action provisions of the AD.

Cost Estimate for Terminating Modification

    Two commenters request that the proposed AD be revised to provide 
correct cost estimates for the optional modification described in 
Airbus Service Bulletin A320-57-1089. The commenters state that the 
service bulletin lists the labor cost as 980 work hours, yet the 
proposed AD provides an estimate of 750 work hours.
    The FAA acknowledges that the service bulletin estimate specifies 
additional work hours (for access and close) that are not included in 
the proposed AD. However, the cost impact information in an AD 
typically describes only the ``direct'' costs of

[[Page 34071]]

specific actions, and does not include incidental costs, such as the 
time required to gain access and close up; planning time; or time 
necessitated by other administrative actions. Because incidental costs 
may vary significantly from operator to operator, they are almost 
impossible to calculate. Additionally, since this is an optional 
modification, operators may choose not to incur such costs, or may 
minimize costs by accomplishing the modification during scheduled 
maintenance. No change is made to the final rule.

Additional Changes to the AD

    To clarify actions for airplanes on which modifications have been 
installed in production and those on which service bulletins have been 
accomplished as retrofit, the FAA has revised paragraph (c)(2) of the 
AD to refer to certain modifications as ``Airbus Production 
Modification * * *.'' Additionally, a heading has been included to 
specify the actions required by paragraphs (c) and (d) of the AD.

Conclusion

    After careful review of the available data, including the comments 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule with the changes previously 
described. The FAA has determined that these changes will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.

Cost Impact

    There are approximately 126 airplanes of U.S. registry that will be 
affected by this AD.
    It takes approximately 60 work hours per airplane to accomplish the 
modification of the rear spar web of the wing, as required by AD 93-08-
15 and retained in this AD, at an average labor rate of $60 per work 
hour. Based on these figures, the total cost impact of the modification 
on U.S. operators is estimated to be $3,600 per airplane.
    It takes approximately 600 work hours per airplane to accomplish 
the cold expansion of certain holes associated with the MLG, as 
required by AD 93-25-13 and retained in this AD, at an average labor 
rate of $60 per work hour. Required parts are provided by the 
manufacturer at no cost to the operators. Based on these figures, the 
total cost impact of the cold expansion on U.S. operators is estimated 
to be $36,000 per airplane.
    The new inspection that is required by this new AD will take 
approximately 24 work hours per airplane to accomplish, at an average 
labor rate of $60 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 $181,440, or $1,440 per airplane, per inspection cycle.
    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.
    Should an operator elect to accomplish the optional terminating 
action specified in this AD, it would take approximately 750 work 
hours, at an average labor rate of $60 per work hour. The required 
parts would cost $27,036; $30,595; or $32,727; depending on the 
airplane configuration. Based on these figures, the cost per airplane 
of the optional terminating action provided by this AD is estimated to 
be $72,036; $75,595; or $77,727.

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

    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

    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 amendments 39-8563 (58 FR 
27923, May 12, 1993) and 39-8777 (59 FR 1903, January 13, 1994), and by 
adding a new airworthiness directive (AD), amendment 39-11739, to read 
as follows:

2000-10-15  Airbus Industrie: Amendment 39-11739. Docket 98-NM-99-
AD. Supersedes AD 93-08-15, Amendment 39-8563; and AD 93-25-13, 
Amendment 39-8777.
    Applicability: Model A320 series airplanes, certificated in any 
category, except those on which 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) has 
been accomplished.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
otherwise modified, altered, or repaired in the area subject to the 
requirements of this AD. For airplanes that have been modified, 
altered, or repaired so that the performance of the requirements of 
this AD is affected, the owner/operator must request approval for an 
alternative method of compliance in accordance with paragraph (f)(1) 
of this AD. The request should include an assessment of the effect 
of the modification, alteration, or repair on the unsafe condition 
addressed by this AD; and, if the unsafe condition has not been 
eliminated, the request should include specific proposed actions to 
address it.

    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 Actions Required by AD 93-08-15

    (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.

Restatement of Actions Required by AD 93-25-13

    (b) For airplanes having MSN's 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,

[[Page 34072]]

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 2: 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 Actions Required by This AD

Ultrasonic Inspections and Corrective Action

    (c) For all airplanes: Perform an ultrasonic inspection to 
detect cracking of the rear spar of the wing, in accordance with 
Airbus Service Bulletin A320-57-1088, Revision 02, dated July 29, 
1999; at the applicable time specified by paragraph (c)(1) or (c)(2) 
of this AD. Repeat the inspection thereafter at intervals not to 
exceed 3,600 flight cycles.
    (1) For airplanes on which the actions specified by Airbus 
Service Bulletin A320-57-1004, Revision 2, dated June 14, 1993, or 
earlier version; and Airbus Service Bulletin A320-57-1060, Revision 
02, dated December 16, 1994, or earlier version; have been 
accomplished: Perform the inspection of all applicable fastener 
holes within 12,000 flight cycles after accomplishment of the 
service bulletins, or within 750 flight cycles after the effective 
date of this AD, whichever occurs later.
    (2) For airplanes on which the actions specified by Airbus 
Production Modification 20740 and Airbus Service Bulletin A320-57-
1060, Revision 2, dated December 16, 1994, or earlier version, have 
been accomplished; or on which Airbus Production Modifications 
20740, 20741, and 20796 have been accomplished: Perform the 
inspections at the locations and applicable times specified by 
paragraphs (c)(2)(i) and (c)(2)(ii) of this AD.
    (i) Perform the inspection of left and right fastener holes 52 
to 55, 82, 83, 87, and 88; located in the rear spar of the wing; 
prior to the accumulation of 17,300 total flight cycles, or within 
750 flight cycles after the effective date of this AD, whichever 
occurs later. If any cracking is found, prior to further flight, 
accomplish the requirements of paragraph (c)(2)(ii) of this AD.
    (ii) Except as required by paragraph (c)(2)(i) of this AD: 
Perform the inspection of all fastener holes located in the rear 
spar of the wing that are not identified in paragraph (c)(2)(i) of 
this AD prior to the accumulation of 20,000 total flight cycles, or 
within 200 flight cycles after the effective date of this AD, 
whichever occurs later.

    Note 3: Accomplishment of the actions specified by Airbus 
Service Bulletin A320-57-1088, dated September 30, 1996, or Revision 
01, dated September 17, 1997, prior to the effective date of this AD 
is acceptable for compliance with the requirements of the initial 
inspection required by paragraph (c) of this AD.

    (d) If any crack is found during any inspection required by 
paragraph (c) of this AD: Prior to 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 (DGAC) (or its 
delegated agent). For a repair method to be approved by the Manager, 
International Branch, ANM-116, as required by this paragraph, the 
Manager's approval letter must specifically reference this AD.

Optional Terminating Action

    (e) Modification of all specified fastener holes in the rear 
spar of the wing in accordance with Airbus Service Bulletin A320-57-
1089, dated December 22, 1996; Revision 01, dated April 17, 1997; or 
Revision 02, dated November 6, 1998; constitutes terminating action 
for the ultrasonic inspections required by paragraph (c) of this AD. 
Such modification, if accomplished prior to the accumulation of 
12,000 total flight cycles, also constitutes terminating action for 
the actions required by paragraphs (a) and (b) of this AD.

Alternative Methods of Compliance

    (f)(1) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, International Branch, ANM-116. 
Operators shall submit their requests through an appropriate FAA 
Principal Maintenance Inspector, who may add comments and then send 
it to the Manager, International Branch, ANM-116.
    (2) Alternative methods of compliance, approved previously in 
accordance with AD 93-25-13; amendment 39-8777, are approved as 
alternative methods of compliance with this AD.

    Note 4: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the International Branch, ANM-116.

Special Flight Permits

    (g) Special flight permits may be issued in accordance with 
sections 21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR 21.197 and 21.199) to operate the airplane to a location where 
the requirements of this AD can be accomplished.

Incorporation by Reference

    (h) Except as required by paragraph (d) of the AD, the actions 
shall be done in accordance with Airbus Service Bulletin A320-57-
1004, Revision 1, dated September 24, 1992; Airbus Service Bulletin 
A320-57-1004, Revision 2, dated June 14, 1993; Airbus Service 
Bulletin A320-57-1060, dated December 8, 1992; Airbus Service 
Bulletin A320-57-1060, Revision 2, dated December 16, 1994; or 
Airbus Service Bulletin A320-57-1088, Revision 02, including 
Appendix 01, dated July 29, 1999; as applicable. Airbus Service 
Bulletin A320-57-1004, Revision 2, dated June 14, 1993, contains the 
following list of effective pages:

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                                             Revision level shown on
                 Page No.                              page                        Date shown on page
----------------------------------------------------------------------------------------------------------------
1, 4, 12, 14, 17-20, 22, 23, 28, 29......  2..........................  June 14, 1993.
15.......................................  1..........................  September 24, 1992.
2, 3, 5-11, 13, 16, 21, 24-27, 30........  Original...................  July 9, 1991.
----------------------------------------------------------------------------------------------------------------

    (1) The incorporation by reference of Airbus Service Bulletin 
A320-57-1004, Revision 2, dated June 14, 1993; Airbus Service 
Bulletin A320-57-1060, Revision 2, dated December 16, 1994; and 
Airbus Service Bulletin A320-57-1088, Revision 02, including 
Appendix 01, dated July 29, 1999; 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 
A320-57-1004, Revision 1, dated September 24, 1992, was approved 
previously by the Director of the Federal Register as of June 
11,1993 (58 FR 27923, May 12, 1993).
    (3) The incorporation by reference of Airbus Service Bulletin 
A320-57-1060, dated December 8, 1992, was approved previously by the 
Director of the Federal Register as of February 14, 1994 (59 FR 
1903, January 13, 1994).
    (4) Copies may be obtained from Airbus Industrie, 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 5: The subject of this AD is addressed in French 
airworthiness directive 1999-264-135(B), dated June 30, 1999.

    (i) This amendment becomes effective on June 30, 2000.


    Issued in Renton, Washington, on May 16, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-12816 Filed 5-25-00; 8:45 am]
BILLING CODE 4910-13-U