[Federal Register Volume 63, Number 122 (Thursday, June 25, 1998)]
[Rules and Regulations]
[Pages 34562-34563]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-16048]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-75-AD; Amendment 39-10606; AD 98-13-18]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain Airbus Model A319 and A321-100 series airplanes, 
that requires 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 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 non-extension of one or more landing gears, 
consequent damage to the airplane structure, and possible injury to 
passengers and crewmembers.

DATES: Effective July 30, 1998.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of July 30, 1998.

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) to include an airworthiness 
directive (AD) that is applicable to certain Airbus Model A319 and 
A321-100 series airplanes was published in the Federal Register on 
April 21, 1998 (63 FR 19678). That action proposed to 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.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the two comments received.
    The commenters support the proposed 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 as proposed.

Cost Impact

    The FAA estimates that 2 airplanes of U.S. registry will be 
affected by this AD, that it will take approximately 20 work hours per 
airplane to accomplish the required actions, and that the average labor 
rate is $60 per work hour. Based on these figures, the cost impact of 
the 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 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.

[[Page 34563]]

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 adding the following new 
airworthiness directive:

98-13-18  Airbus Industrie: Amendment 39-10606. 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 
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.
    (d) The actions shall be done in accordance with Airbus 
Industrie A319/A321 All Operator Telex (AOT) 32-15, dated July 1, 
1997. This incorporation by reference was approved by the Director 
of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR 
part 51. 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 97-177-101(B), dated August 13, 1997.

    (e) This amendment becomes effective on July 30, 1998.

    Issued in Renton, Washington, on June 11, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-16048 Filed 6-24-98; 8:45 am]
BILLING CODE 4910-13-U