[Federal Register Volume 63, Number 76 (Tuesday, April 21, 1998)]
[Proposed Rules]
[Pages 19678-19680]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-10476]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-75-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A319 and A321-100 Series 
Airplanes

AGENCY: Federal Aviation Administration, DOT.


[[Page 19679]]


ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the adoption of a new airworthiness 
directive (AD) that is applicable to certain Airbus Model A319 and 
A321-100 series airplanes. This proposal would require adjustment of 
the landing gear unlocked-stop screw; replacement of the shear pins in 
the reduction gear box and the landing gear pulley assembly with new or 
serviceable shear pins; a one-time inspection to detect discrepancies 
of the landing gear cut-out valve; an operational test of the uplock 
mechanical control system; and follow-on corrective actions, 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 non-extension of one or more landing gears, consequent damage 
to the airplane structure, and possible injury to passengers and 
crewmembers.

DATES: Comments must be received by May 21, 1998.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 98-NM-75-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-75-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-75-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    The Direction Generale de l'Aviation Civile (DGAC), which is the 
airworthiness authority for France, notified the FAA that an unsafe 
condition may exist on certain Airbus Model A319 and A321-100 series 
airplanes. The DGAC advises that certain Airbus Model A319 and A321-100 
series airplanes were manufactured with the free-fall control mechanism 
for the landing gear rigged incorrectly. The landing gear unlocked-stop 
screw of the reduction gear box was not adjusted properly. Such 
improper adjustment of the landing gear unlocked-stop screw could lead 
to damage to the cut-out valve and rupture of the four shear pins in 
the free-fall mechanism during a free-fall extension. This condition, 
if not corrected, could result in non-extension of one or more landing 
gears, consequent damage to the airplane structure, and possible injury 
to passengers and crewmembers.

Explanation of Relevant Service Information

    The manufacturer has issued Airbus Industrie A319/A321 All Operator 
Telex (AOT) 32-15, dated July 1, 1997, which describes procedures for 
adjustment of the landing gear unlocked-stop screw; replacement of the 
shear pins in the reduction gear box and the landing gear pulley 
assembly with new or serviceable shear pins; a one-time visual 
inspection of the main landing gear cut-out valve to detect 
discrepancies (rupture, distortion, and angular position); an 
operational test of the uplock mechanical control system; and follow-on 
corrective actions, if necessary. The corrective actions include 
replacing the cut-out valve with a new or serviceable part and 
performing functional tests of the normal extension and retraction of 
the landing gear and of the free-fall extension system. Accomplishment 
of the actions specified in the AOT is intended to adequately address 
the identified unsafe condition. The DGAC classified this AOT as 
mandatory and issued French airworthiness directive 97-177-101(B), 
dated August 13, 1997, in order to assure 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 
Sec. 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 require accomplishment of 
the actions specified in the AOT described previously.

Cost Impact

    The FAA estimates that 2 airplanes of U.S. registry would be 
affected by this proposed AD, that it would take approximately 20 work 
hours per airplane to accomplish the proposed actions, and that the 
average labor rate is $60 per work hour. Based on these figures, the 
cost impact of the proposed AD on U.S. operators is estimated to be 
$2,400, or $1,200 per airplane.
    The cost impact figure discussed above is based on assumptions that 
no operator has yet accomplished any of the proposed requirements of 
this AD action, and that no operator would

[[Page 19680]]

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 adding the following new 
airworthiness directive:

Airbus Industrie: Docket 98-NM-75-AD.

    Applicability: Model A319 series airplanes, manufacturer's 
serial numbers 578 through 625 inclusive; and Model A321-100 series 
airplanes, manufacturer's serial numbers 385 through 620 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 (b) 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 non-extension of one or more landing gears, 
consequent damage to the airplane structure, and possible injury to 
passengers and crewmembers, accomplish the following:
    (a) Within 400 flight hours after the effective date of this AD, 
accomplish the actions required by paragraphs (a)(1), (a)(2), 
(a)(3), and (a)(4) of this AD, in accordance with Airbus Industrie 
A319/A321 All Operator Telex (AOT) 32-15, dated July 1, 1997.
    (1) Adjust the landing gear unlocked-stop screw.
    (2) Replace the shear pins in the reduction gear box and the 
landing gear pulley assembly with new or serviceable shear pins.
    (3) Inspect the cut-out valve for discrepancies. If any 
discrepancy to the cut-out valve is detected, accomplish the 
requirements of paragraphs (a)(3)(i) and (a)(3)(ii) of this AD at 
the time specified in the AOT.
    (i) Replace the cut-out valve with a new or serviceable part 
within the time specified in the AOT.
    (ii) After replacing the cut-out valve, perform a functional 
test of the normal extension and retraction of the landing gear and 
of the free-fall extension system. If any discrepancy is detected 
during the accomplishment of either of the functional tests, prior 
to further flight, repair in accordance with the AOT.
    (4) Perform an operational test of the gear uplock and door 
uplock mechanical control system. If any discrepancy is detected 
during the accomplishment of the operational test, prior to further 
flight, repair in accordance with the AOT.
    (b) 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.

    (c) 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.

    Note 3: The subject of this AD is addressed in French 
airworthiness directive 97-177-101(B), dated August 13, 1997.

    Issued in Renton, Washington, on April 15, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-10476 Filed 4-20-98; 8:45 am]
BILLING CODE 4910-13-U