[Federal Register Volume 64, Number 11 (Tuesday, January 19, 1999)]
[Rules and Regulations]
[Pages 2817-2819]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-911]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-215-AD; Amendment 39-11001; AD 99-02-10]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A320 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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

SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD), applicable to certain Airbus Model A320 series airplanes, that 
currently requires modification of the trimmable horizontal stabilizer 
(THS). This amendment adds a requirement for a one-time inspection of 
the flexible hoses of the elevator return lines on the THS to detect 
installation of incorrect clamps, or missing clamps or bonding leads; 
and for replacement of the clamps or bonding leads with new parts, if 
necessary. 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 
leakage from hydraulic pipe fittings in the THS, which could result in 
failure of the THS and consequent reduced controllability of the 
airplane.

DATES: Effective February 23, 1999.
    The incorporation by reference of certain publications as listed in 
the regulations, is approved by the Director of the Federal Register as 
of February 23, 1999.
    The incorporation by reference of certain other publications as 
listed in the regulations, was approved previously by the Director of 
the Federal Register as of September 21, 1995 (60 FR 43519, August 22, 
1995).

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 95-17-12, 
amendment 39-9342 (60 FR 43519, August 22, 1995), which is applicable 
to certain Airbus Model A320 series airplanes, was published in the 
Federal Register on October 15, 1998 (63 FR 55352). The action proposed 
to continue to require modification of the trimmable horizontal 
stabilizer (THS). In addition, the action proposed to add requirements 
for a one-time inspection of the flexible hoses of the elevator return 
lines on the THS to detect installation of incorrect clamps, or missing 
clamps or bonding leads; and for replacement of the clamps or bonding 
leads with new parts, if necessary.

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.
    Two commenters indicate that they are not affected by the proposed 
rule.

Request To Revise Applicability of the AD

    Two commenters request that the applicability of the proposed AD be 
revised to exclude airplanes on which Airbus Service Bulletin A320-29-
1058, Revision 1, dated November 28, 1994, has been accomplished. One 
commenter, an operator, notes that it has already modified its fleet in 
accordance with Revision 1 of the service bulletin, which provides for 
installation of clamps having the correct part numbers. Therefore, the 
operator states that the additional one-time inspection to detect 
installation of incorrect clamps, as proposed in the AD, should not be 
required for its fleet.
    Another commenter, the manufacturer, suggests a revision to 
paragraph (a) of the proposed AD to delete references to Airbus 
Modifications 22621 and 23556, and a revision to paragraph (c) of the 
proposed AD to narrow its applicability to those airplanes on which 
Airbus Modification 23556 has been installed in production, or on which 
Airbus Service Bulletin A320-29-1058, dated July 16, 1993, has been 
accomplished. The manufacturer states that these changes would 
correctly exclude airplanes on which Revision 1 of service bulletin 
A320-29-1058 has been accomplished.
    The FAA concurs that airplanes on which Revision 1 of the 
referenced service bulletin has been accomplished

[[Page 2818]]

are not affected by the new requirements of the AD. The applicability 
in the proposed AD correctly specifies effectivity based on 
manufacturer serial numbers, as did the effectivity of the parallel 
French airworthiness directive. However, the FAA has determined that 
the applicability may be narrowed to exclude airplanes on which 
Revision 1 of service bulletin A320-29-1058 has been accomplished, and 
has revised the final rule accordingly. Although the changes suggested 
by the manufacturer have not been incorporated verbatim, the FAA has 
determined that the final rule, as revised, will meet the intent of the 
changes proposed by these commenters.

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 change previously 
described. The FAA has determined that this change 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.
    The modification that is currently required by AD 95-17-12, takes 
approximately 13 work hours per airplane to accomplish, 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 
cost impact of the currently required actions on U.S. operators is 
estimated to be $98,280, or $780 per airplane.
    The inspection that is required by this new AD will take 
approximately 5 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 required inspection of this AD on U.S. operators is 
estimated to be $37,800, or $300 per airplane.
    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.

Regulatory Impact

    The regulations adopted herein will not have substantial direct 
effects 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, in 
accordance with Executive Order 12612, it is determined that this final 
rule does not have sufficient federalism implications to warrant the 
preparation of a Federalism Assessment.
    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 39-9342 (60 FR 
43519, August 22, 1995), and by adding a new airworthiness directive 
(AD), amendment 39-11001, to read as follows:

99-02-10  Airbus Industrie: Amendment 39-11001. Docket 98-NM-215-AD. 
Supersedes AD 95-17-12, Amendment 39-9342.

    Applicability: Model A320 series airplanes; serial numbers 002 
through 008 inclusive, 010 through 014 inclusive, 016 through 078 
inclusive, 080 through 104 inclusive, 106 through 363 inclusive, 365 
through 384 inclusive, 386 through 411 inclusive, 413 through 433 
inclusive, 435 through 457 inclusive, 459 through 467 inclusive, and 
469 through 472 inclusive; except for airplanes on which Airbus 
Service Bulletin A320-29-1058, Revision 1, dated November 28, 1994, 
has been accomplished; certificated in any category.

    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 (d) 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 leakage from hydraulic pipe fittings in the trimmable 
horizontal stabilizer (THS), which could result in failure of the 
THS and consequent reduced controllability of the airplane, 
accomplish the following:
    (a) For airplanes on which Airbus Modification 22621 and Airbus 
Modification 23556 have not been installed: Within 3,500 flight 
hours after September 21, 1995 (the effective date of AD 95-17-12), 
modify the THS in accordance with Airbus Service Bulletin A320-29-
1058, dated July 16, 1993, or Revision 1, dated November 28, 1994, 
and Airbus Service Bulletin A320-27-1041, Revision 2, dated April 
20, 1994. After the effective date of this AD, only Revision 1 of 
Airbus Service Bulletin A320-29-1058 shall be used.
    (b) For airplanes other than those identified in paragraph (a) 
of this AD: Within 3,500 flight hours after the effective date of 
this AD, modify the THS in accordance with Airbus Service Bulletin 
A320-29-1058, Revision 1, dated November 28, 1994, and Airbus 
Service Bulletin A320-27-1041, Revision 2, dated April 20, 1994.
    (c) Within 500 flight hours after the effective date of this AD, 
perform a one-time inspection of the flexible hoses of the elevator 
return lines on the THS to detect installation of incorrect clamps, 
or missing clamps or bonding leads, in accordance with Airbus All 
Operator Telex (AOT) 29-10, Revision 02, dated February 13, 1995.
    (1) If the correct clamps are installed, and there are no 
missing clamps or bonding leads, no further action is required by 
paragraph (b) of this AD.
    (2) If any incorrect clamp is installed, prior to further 
flight, replace the incorrect clamp with the correct clamp; and, if 
any bonding lead is missing, prior to further flight, install a new 
bonding lead, in accordance with the AOT.
    (3) If any clamp or bonding lead is missing, prior to further 
flight, install new parts in accordance with the AOT.
    (d) 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.

    Note 2: Information concerning the existence of approved 
alternative methods of

[[Page 2819]]

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

    (e) 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.
    (f) The inspection shall be done in accordance with Airbus All 
Operator Telex (AOT) 29-10, Revision 02, dated February 13, 1995. 
The modification shall be done in accordance with Airbus Service 
Bulletin A320-29-1058, dated July 16, 1993; Airbus Service Bulletin 
A320-29-1058, Revision 1, dated November 28, 1994; and Airbus 
Service Bulletin A320-27-1041, Revision 2, dated April 20, 1994; as 
applicable.
    (1) The incorporation by reference of Airbus Service Bulletin 
A320-29-1058, Revision 1, dated November 28, 1994, and Airbus All 
Operator Telex (AOT) 29-10, Revision 02, dated February 13, 1995, 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 
A320-29-1058, dated July 16, 1993, and Airbus Service Bulletin A320-
27-1041, Revision 2, dated April 20, 1994, was approved previously 
by the Director of the Federal Register as of September 21, 1995 (60 
FR 43519, August 22, 1995).
    (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 3: The subject of this AD is addressed in French 
airworthiness directive 93-123-046(B)R1, dated May 10, 1995.

    (g) This amendment becomes effective on February 23, 1999.

    Issued in Renton, Washington, on January 8, 1999.
John J. Hickey,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 99-911 Filed 1-15-99; 8:45 am]
BILLING CODE 4910-13-P