[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]
-----------------------------------------------------------------------
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.
-----------------------------------------------------------------------
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
