AD 2002-03-11

[Federal Register Volume 67, Number 29 (Tuesday, February 12, 2002)]
[Rules and Regulations]
[Pages 6390-6393]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 02-3455]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-413-AD; Amendment 39-12652; AD 2002-03-11]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A319, A320, and A321 
Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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

SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD), applicable to certain Airbus Model A319, A320, and A321 series 
airplanes, that currently requires a one-time ultrasonic inspection to 
detect disbonding of the skin attachments at the stringers and spars of 
the vertical stabilizer, repair, if necessary, and, for certain 
airplanes, prior or concurrent modification of the vertical stabilizer 
to ensure proper reinforcement of its attachment to the skin. This 
amendment adds repetitive ultrasonic inspections of the subject area, 
and repair, if necessary. It also adds installation of fasteners to 
reinforce the bonds to the skin, which terminates the repetitive 
inspections. 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 prevent 
failure of the bonds of the vertical stabilizer spar boxes to the skin, 
which could lead to reduced structural integrity of the spar boxes.

DATES: Effective March 19, 2002.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of March 19, 2002.
    The incorporation by reference of certain other publications listed 
in the regulations was approved previously by the Director of the 
Federal Register as of June 28, 2000 (65 FR 37029, June 13, 2000).

[[Page 6391]]


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: 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 2000-11-27, 
amendment 39-11776 (65 FR 37029, June 13, 2000), which is applicable to 
certain Airbus Model A319, A320, and A321 series airplanes, was 
published in the Federal Register on September 4, 2001 (66 FR 46243). 
The action proposed to continue to require a one-time ultrasonic 
inspection to detect disbonding of the skin attachments at the 
stringers and spars of the vertical stabilizer, and repair, if 
necessary. For certain airplanes, the action also proposed to continue 
to require prior or concurrent modification of the vertical stabilizer 
to ensure proper reinforcement of its attachment to the skin. The 
action proposed to add repetitive ultrasonic inspections of the subject 
area, and repair, as necessary. It also proposed to add installation of 
fasteners to reinforce the bonds to the skin, which would terminate the 
repetitive inspections.

Comments

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

Remove Modification Number From Applicability Statement

    One commenter, the airplane manufacturer, requests that the FAA 
revise the proposed AD to remove the modification number from the 
applicability statement. The commenter notes that the referenced 
modification is not valid for production airplanes.
    The FAA concurs with the commenter's request and has revised the 
applicability statement of this final rule accordingly. We find that 
this change does not expand the scope of the proposed AD but merely 
provides clarification by eliminating redundancy.

Give Credit for Fastener Installation per Other Service Information

    One commenter requests that we revise the proposed AD to refer to 
Airbus Service Bulletin A320-55-1028, Revision 02, dated July 26, 2000, 
as an acceptable source of service information for accomplishment of 
the installation of fasteners specified in paragraph (f) of the 
proposed AD. Paragraph (f) of the proposed AD refers to Airbus Service 
Bulletin A320-55-1028, Revision 03, dated November 2, 2000, as the 
appropriate source of service information for the installation of new 
fasteners. The commenter states that no substantive procedural changes 
were made from Revision 02 to Revision 03 of the service bulletin, and 
no additional work is necessary for airplanes on which Revision 02 was 
accomplished. Revision 03 merely clarifies recommendations for repeat 
inspections if the modification is only partially accomplished.
    We concur with the commenter's request for the reasons specified by 
the commenter. Also, since the issuance of the proposed AD, Airbus has 
issued Service Bulletin A320-55-1028, Revision 04, dated April 13, 
2001. The procedures in Revision 04 of the service bulletin are 
essentially the same as those in Revision 03. Therefore, we have 
revised paragraph (f) of this AD to specify that fastener installation 
must be accomplished in accordance with Airbus Service Bulletin A320-
55-1028, Revision 04. Also, we have added a new note, Note 2, to this 
final rule and renumbered subsequent notes accordingly, to give credit 
for accomplishment of the installation of fasteners prior to the 
effective date of this AD in accordance with Airbus Service Bulletin 
A320-55-1028, Revision 02 (based on the commenter's request), or 
Revision 03. We have also revised the applicability statement of this 
final rule to exclude airplanes on which Airbus Service Bulletin A320-
55-1028, Revision 02, Revision 03, or Revision 04, has been 
accomplished, from the applicability of this AD. (The applicability 
statement of the proposed AD states that airplanes on which Airbus 
Service Bulletin A320-55-1028, Revision 03, has been accomplished are 
not subject to this AD.)

Request To Revise Proposed Compliance Time for Modification

    The commenter requests that we revise the compliance time of 
paragraph (f) of the proposed AD to refer to ``5 years from the `entry 
in service' of the airplane'' instead of ``5 years after the date of 
manufacture of the airplane.'' The commenter points out that the date 
of manufacture is the date of the first flight of the airplane, whereas 
the date of ``entry into service'' is the date of delivery of the 
airplane. The difference between these dates could be one month or 
more. The commenter recommends that we make this change to avoid 
operator questions.
    We do not concur. For clarification, we define the ``date of 
manufacture'' as the date of issuance of the Certificate of 
Airworthiness. We find that this constitutes a definitive date when all 
of the manufacturing processes are completed. We have determined that 
this date should be readily discernible by operators, and no change to 
the final rule is necessary in this regard.

Explanation of Additional Changes to Final Rule

    In addition to the changes described previously, several 
typographical errors have been corrected in this final rule.

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 23 Model A319, A320, and A321 series 
airplanes of U.S. registry that will be affected by this AD.
    The repetitive inspections in this AD will take approximately 3 to 
7 work hours per airplane to accomplish, at an average labor rate of 
$60 per work hour. Based on these figures, the cost impact on U.S. 
operators of the repetitive inspections required by this AD is 
estimated to be $4,140 to $9,660, or $180 to $420 per airplane, per 
inspection cycle.
    The installation of fasteners in this AD will take approximately 5 
to 480 work hours per airplane to accomplish, depending upon the 
configuration of the airplane, at an average labor rate of $60 per work 
hour. Required parts will be provided by the airplane manufacturer at 
no cost to operators. Based on these figures, the cost impact on U.S. 
operators of the installation required in this AD is estimated to be 
$6,900 to $662,400, or $300 to $28,800 per airplane.

[[Page 6392]]

    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. 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 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 amendment 39-11776 (65 FR 
37029, June 13, 2000), and by adding a new airworthiness directive 
(AD), amendment 39-12652, to read as follows:

2002-03-11  Airbus Industrie: Amendment 39-12652. Docket 2000-NM-
413-AD. Supersedes AD 2000-11-27, Amendment 39-11776.

    Applicability: Model A319, A320, and A321 series airplanes; 
certificated in any category; as listed in Airbus Service Bulletin 
A320-55A1027, dated May 13, 2000, Revision 01, dated August 1, 2000, 
or Revision 02, dated February 13, 2001; except those airplanes on 
which Airbus Service Bulletin A320-55-1028, Revision 02, dated July 
26, 2000, Revision 03, dated November 2, 2000, or Revision 04, dated 
April 13, 2001; has been accomplished.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
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 (g)(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 prevent failure of the bonds of the vertical stabilizer spar 
box to the skin, which could lead to reduced structural integrity of 
the spar boxes, accomplish the following:

Restatement of Requirements of AD 2000-11-27

Ultrasonic Inspection

    (a) Within 60 days after June 28, 2000 (the effective date of AD 
2000-11-27, amendment 39-11776): Perform a one-time ultrasonic 
inspection to detect disbonding (damage) of the skin attachments at 
the stringers and spars of the vertical stabilizer, left- and right-
hand sides, in accordance with Airbus Service Bulletin A320-55A1027, 
dated May 13, 2000; Revision 01, dated August 1, 2000; or Revision 
02, dated February 13, 2001.

Modification (for Certain Airplanes)

    (b) For airplanes with manufacturer's serial numbers listed in 
paragraph B of the Planning Information of Airbus Service Bulletin 
A320-55A1027, dated May 13, 2000; Revision 01, dated August 1, 2000; 
or Revision 02, dated February 13, 2001: Prior to or concurrent with 
the ultrasonic inspection required by paragraph (a) of this AD, 
modify the vertical stabilizer to ensure proper reinforcement of the 
structure/skin attachments, in accordance with Airbus Service 
Bulletin A320-55-1026, Revision 01, dated May 20, 1999.

New Requirements of This AD

Repetitive Inspections and Repair, If Necessary

    (c) Within 1,100 flight cycles from the previous inspection 
performed in accordance with paragraph (a) of this AD, or 60 days 
after the effective date of this AD, whichever occurs later: Perform 
an ultrasonic inspection to detect disbonding of the skin attachment 
at the spars and the stringers of the vertical stabilizer spar box, 
in accordance with Airbus Service Bulletin A320-55A1027, dated May 
13, 2000; Revision 01, dated August 1, 2000; or Revision 02, dated 
February 13, 2001.
    (d) If no damage is detected, or if only a single area of damage 
is found and it is less than or equal to an area of 300 square 
millimeters (mm\2\) during any ultrasonic inspection required by 
this AD, repeat the ultrasonic inspection thereafter at intervals 
not to exceed 1,100 flight cycles.
    (e) If any damage is detected and the area of damage found is 
greater than 300 mm\2\, or if multiple areas of damage are found on 
one specific component (stringer/spar attachment) during any 
ultrasonic inspection required by this AD, prior to further flight, 
accomplish applicable repairs in accordance with Airbus Service 
Bulletin A320-55A1027, dated May 13, 2000; Revision 01, dated August 
1, 2000; or Revision 02, dated February 13, 2001. Repeat the 
ultrasonic inspection thereafter at intervals not to exceed 1,100 
flight cycles.

Modification

    (f) Within 5 years after the date of manufacture of the 
airplane: Install fasteners to reinforce the attachment between the 
skin panel and areas of the vertical stabilizer affected by 
disbonding, in accordance with Airbus Service Bulletin A320-55-1028, 
Revision 04, dated April 13, 2001. Accomplishment of the 
installation terminates the repetitive inspections required by 
paragraph (c) of this AD.

    Note 2: Installations accomplished prior to the effective date 
of this AD in accordance with Airbus Service Bulletin A320-55-1028, 
Revision 02, dated July 26, 2000, or Revision 03, dated November 2, 
2000, are considered acceptable for compliance with paragraph (f) of 
this AD.

Alternative Methods of Compliance

    (g)(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, FAA, 
Transport Airplane Directorate. 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 2000-11-27, amendment 39-11776, are approved as 
alternative methods of compliance with paragraphs (a) and (b) of 
this AD.

    Note 3: Information concerning the existence of approved 
alternative methods of

[[Page 6393]]

compliance with this AD, if any, may be obtained from the 
International Branch, ANM-116.

Special Flight Permits

    (h) Special flight permits may be issued in accordance with 
Secs. 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

    (i) The actions shall be done in accordance with Airbus Service 
Bulletin A320-55-1026, Revision 01, dated May 20, 1999; Airbus 
Service Bulletin A320-55A1027, dated May 13, 2000, Airbus Service 
Bulletin A320-55A1027, Revision 01, dated August 1, 2000, or Airbus 
Service Bulletin A320-55A1027, Revision 02, dated February 13, 2001; 
and Airbus Service Bulletin A320-55-1028, Revision 04, dated April 
13, 2001.
    (1) The incorporation by reference of Airbus Service Bulletin 
A320-55A1027, Revision 01, dated August 1, 2000; Airbus Service 
Bulletin A320-55A1027, Revision 02, dated February 13, 2001; and 
Airbus Service Bulletin A320-55-1028, Revision 04, dated April 13, 
2001; 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 
A320-55-1026, Revision 01, dated May 20, 1999; and Airbus Service 
Bulletin A320-55A1027, dated May 13, 2000; was approved previously 
by the Director of the Federal Register as of June 28, 2000 (65 FR 
37029, June 13, 2000).
    (3) 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 4: The subject of this AD is addressed in French 
airworthiness directive 2000-520-159(B), dated December 13, 2000.

Effective Date

    (j) This amendment becomes effective on March 19, 2002.

    Issued in Renton, Washington, on February 7, 2002.
Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 02-3455 Filed 2-11-02; 8:45 am]
BILLING CODE 4910-13-P