[Federal Register Volume 68, Number 246 (Tuesday, December 23, 2003)]
[Rules and Regulations]
[Pages 74176-74177]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-31271]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NM-61-AD; Amendment 39-13398; AD 2003-26-02]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A319-113 and -114 Series 
Airplanes; and Model A320-111, -211, and -212 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 all Airbus Model A319-113 and -114 series airplanes; and 
Model A320-111, -211, and -212 series airplanes; that requires either a 
review of airplane maintenance or delivery records, or one-time 
inspection of the hydraulic actuators located in the pivot doors of 
both thrust reversers to identify the part number, and eventual 
replacement of certain actuators with modified or new actuators. This 
action is necessary to prevent jamming of a thrust reverser door during 
operation, or inadvertent deployment of a thrust reverser door in-
flight, which could result in reduced controllability of the airplane. 
This action is intended to address the identified unsafe condition.

DATES: Effective January 27, 2004.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of January 27, 2004.

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, 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: Tim Dulin, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2141; 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 all Airbus Model A319-113 and -114 
series airplanes; and Model A320-111, -211, and -212 series airplanes; 
was published in the Federal Register on October 2, 2003 (68 FR 56792). 
That action proposed to require either a review of airplane maintenance 
or delivery records, or one-time inspection of the hydraulic actuators 
located in the pivot doors of both thrust reversers to identify the 
part number, and eventual replacement of certain actuators with 
modified or new actuators.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were submitted in response 
to the proposal or the FAA's determination of the cost to the public.

Conclusion

    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 108 airplanes of U.S. registry will be 
affected by this AD, that it will take approximately 8 work hours per 
airplane to accomplish the required actions, and that the average labor 
rate is $65 per work hour. Based on these figures, the cost impact of 
the AD on U.S. operators is estimated to be $56,160, or $520 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. The cost impact figures discussed 
in AD rulemaking actions represent only the time necessary to perform 
the specific actions actually required by the AD. These figures 
typically do not include incidental costs, such as the time required to 
gain access and close up, planning time, or time necessitated by other 
administrative actions.

Regulatory Impact

    The regulations adopted herein will not have a substantial direct 
effect 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, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    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

[[Page 74177]]

``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

0
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

0
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]

0
2. Section 39.13 is amended by adding the following new airworthiness 
directive:

2003-26-02 Airbus: Amendment 39-13398. Docket 2002-NM-61-AD.

    Applicability: All Model A319-113 and -114 series airplanes; and 
Model A320-111, -211, and -212 series airplanes; certificated in any 
category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent jamming of a thrust reverser door during operation or 
inadvertent deployment of a thrust reverser door in-flight, which 
could result in reduced controllability of the airplane, accomplish 
the following:

Inspection and Follow-on Actions

    (a) Within 500 airplane flight cycles after the effective date 
of this AD: Do a detailed inspection of the eight hydraulic 
actuators located in the pivot doors of the thrust reversers (one 
actuator per pivot door, four pivot doors per thrust reverser, two 
thrust reversers per airplane) to identify the part number (P/N) of 
each actuator, in accordance with Airbus Service Bulletin A320-78-
1020, excluding Appendix 01, dated March 28, 2001. Instead of a 
detailed inspection of the hydraulic actuators, a review of airplane 
maintenance and delivery records is acceptable if the P/N of each 
actuator installed on the airplane can be positively determined from 
that review.

    Note 1: For the purposes of this AD, a detailed inspection is 
defined as: ``An intensive visual examination of a specific 
structural area, system, installation, or assembly to detect damage, 
failure, or irregularity. Available lighting is normally 
supplemented with a direct source of good lighting at intensity 
deemed appropriate by the inspector. Inspection aids such as mirror, 
magnifying lenses, etc., may be used. Surface cleaning and elaborate 
access procedures may be required.''

    (1) For any actuator having P/Ns D23090000-1, D23090000-2, 
D23090000-3, or D23090000-4: Prior to the accumulation of 20,000 
total actuator flight cycles, or within 250 airplane flight cycles 
after accomplishment of the detailed inspection or airplane records 
review required by paragraph (a) of this AD, whichever occurs later, 
replace the actuator with a modified or new actuator having part 
number D23090000-5 or D23090000-6, in accordance with the service 
bulletin.
    (2) For any actuator having P/N D23090000-5: Prior to the 
accumulation of 30,000 total actuator flight cycles, or within 250 
airplane flight cycles after the detailed inspection or airplane 
records review required by paragraph (a) of this AD, whichever 
occurs later, replace the actuator with a modified or new actuator 
having P/N D23090000-6, in accordance with the service bulletin.
    (3) For any actuator having P/N D23090000-6: No further action 
is required by this paragraph.

    Note 2: Airbus Service Bulletin A320-78-1020 references Rohr 
CFM56-5A Service Bulletin RA32078-106, dated November 16, 2000, as 
an additional source of service information for modification of the 
actuators.

    (b) Once all of the actuators located in the pivot doors of the 
thrust reversers have P/N D23090000-6, no further action is required 
by paragraph (a) of this AD.
    (c) For operators that do not track actuator flight cycles, or 
do not have a means of obtaining information regarding actuator 
flight cycles, engine flight cycles must be used instead of actuator 
flight cycles.

Parts Installation

    (d) As of the effective date of this AD, no person may install 
an actuator having P/N D23090000-1, D23090000-2, D23090000-3, or 
D23090000-4 on any airplane.

Submission of Inspection Results to Manufacturer Not Required

    (e) Although the service bulletin referenced in this AD 
specifies to submit information to the manufacturer, this AD does 
not include such a requirement.

Alternative Methods of Compliance

    (f) In accordance with 14 CFR 39.19, the Manager, International 
Branch, ANM-116, FAA, Transport Airplane Directorate, is authorized 
to approve alternative methods of compliance for this AD.

Incorporation by Reference

    (g) The actions must be done in accordance with Airbus Service 
Bulletin A320-78-1020, excluding Appendix 01, dated March 28, 2001. 
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 2001-361(B) R1, dated September 3, 2003.

Effective Date

    (h) This amendment becomes effective on January 27, 2004.

    Issued in Renton, Washington on December 12, 2003.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 03-31271 Filed 12-22-03; 8:45 am]
BILLING CODE 4910-13-P