[Federal Register Volume 63, Number 199 (Thursday, October 15, 1998)]
[Proposed Rules]
[Pages 55352-55354]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-27596]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-215-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model 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 certain Airbus Model A320 
series airplanes, that currently requires modification of the trimmable 
horizontal stabilizer (THS). This action would 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. This proposal is prompted by 
issuance of mandatory continuing airworthiness information by a foreign 
civil airworthiness authority. The actions specified by the proposed 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: Comments must be received by November 16, 1998.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 98-NM-215-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9:00 a.m. and 3:00 p.m., Monday through Friday, except 
Federal holidays.
    The service information referenced in the proposed rule may be 
obtained from Airbus Industrie, 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: 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:

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 notice may be changed in 
light of the comments received.
    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 notice must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 98-NM-215-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. 98-NM-215-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    On August 11, 1995, the FAA issued AD 95-17-12, amendment 39-9342 
(60 FR 43519, August 22, 1995), applicable to certain Airbus Model A320 
series airplanes, to require modification of the trimmable horizontal 
stabilizer (THS). That action was prompted by a report of leakage from 
some of the hydraulic pipe fittings after a lightning strike. The 
requirements of that AD are intended to prevent such leakage from 
hydraulic pipe fittings, which could result in the loss of the pilot's 
ability to control the moveable surfaces of the THS.

Actions Related to Previous Rule

    In relation to the actions required by AD 95-17-12, the Direction 
Generale de l'Aviation Civile (DGAC), which is the airworthiness 
authority for France, notified the FAA that incorrect clamps were 
installed on certain Airbus Model A320 series airplanes, in accordance 
with Airbus Service Bulletin A320-29-1058, dated July 16, 1993. (That 
service bulletin was referenced in AD 95-17-12 as the appropriate 
source of service information for modification of the trimmable 
horizontal stabilizer.) The clamps referenced in that service bulletin 
were made for rigid hoses and not for correction of leakage in the 
flexible hoses, as required by AD 95-17-12. As a result of these 
findings, Airbus issued All Operator Telex (AOT) 29-10, dated June 15, 
1994, which identified the correct clamps to use with the flexible 
hoses. The AOT also excluded a number of airplanes from the affected 
list because the correct clamps had been incorporated during 
production. Upon further investigation, however, the manufacturer 
discovered that incorrect clamps were installed on some of the 
airplanes that had been excluded.
    Consequently, Airbus issued AOT 29-10, Revision 01, dated September 
23, 1994, to provide procedures for inspection for installation of 
incorrect clamps on those airplanes that were identified as having been 
modified

[[Page 55353]]

during production. Subsequent investigation revealed that some of the 
airplanes modified in accordance with Revision 01 of the AOT were 
missing the clamps or bonding leads required for proper electrical 
contact with the flexible hoses of the elevator return lines.

Explanation of Relevant Service Information

    Airbus has issued AOT 29-10, Revision 02, dated February 13, 1995, 
which describes procedures for a one-time inspection of the flexible 
hoses of the elevator return lines on the THS to detect installation of 
incorrect clamps, and missing clamps or bonding leads. That AOT also 
describes procedures for replacement of the clamps or bonding leads 
with new parts, if necessary.
    Airbus also has issued Service Bulletin A320-29-1058, Revision 1, 
dated November 28, 1994, which updates the original issue of the 
service bulletin by specifying new, correct clamps for accomplishment 
of Airbus Modification 23556.
    Accomplishment of the actions specified in the service information 
is intended to adequately address the identified unsafe condition. The 
DGAC classified this service information as mandatory and issued French 
airworthiness directive 93-123-046(B)R1, dated May 10, 1995, 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 supersede AD 95-17-12 to 
continue to require modification of the THS. In addition, this proposed 
AD would 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, and missing clamps or bonding leads; and for 
replacement of the clamps or bonding leads with new parts, if 
necessary. The actions would be required to be accomplished in 
accordance with the service information described previously.

Cost Impact

    There are approximately 126 airplanes of U.S. registry that would 
be affected by this proposed 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 modification on U.S. operators is 
estimated to be $98,280, or $780 per airplane.
    The inspection that is proposed in this AD action would 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 proposed 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 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.

Regulatory Impact

    The regulations proposed herein would 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 
proposal would not have sufficient federalism implications to warrant 
the preparation of a Federalism Assessment.
    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 39-9342 (60 FR 
43519, August 22, 1995), and by adding a new airworthiness directive 
(AD), to read as follows:

Airbus Industrie: 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; certificated in any category.

    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 (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

[[Page 55354]]

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 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.

    Note 3: The subject of this AD is addressed in French 
airworthiness directive 93-123-046(B)R1, dated May 10, 1995.

    Issued in Renton, Washington, on October 5, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-27596 Filed 10-14-98; 8:45 am]
BILLING CODE 4910-13-U