[Federal Register Volume 69, Number 6 (Friday, January 9, 2004)]
[Rules and Regulations]
[Pages 1509-1511]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-123]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-120-AD; Amendment 39-13416; AD 2004-01-03]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A319, A320, and A321 
Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD), applicable to certain Airbus Model A320 series airplanes, that 
currently requires an inspection to detect moisture and migrated 
bushings of the guide fittings of the safety locking pins of the 
passenger doors, removal of any moisture, application of grease, and 
reinstallation of any migrated bushing. That AD also requires 
installation of a greasing nipple on the guide fitting of the locking 
pin and on three telescopic rods on the passenger doors. This amendment 
adds a requirement for modification of the upper guide fitting of the 
locking pin, and expands the applicability in the existing AD. The 
actions specified by this AD are intended to prevent jamming of the 
locking pin of the passenger door, which could result in inability to 
open the passenger door and delay of evacuation in an emergency, 
resulting in possible injury to passengers or crew. This action is 
intended to address the identified unsafe condition.

DATES: Effective February 13, 2004.
    The incorporation by reference of a certain publication, as listed 
in the regulations, is approved by the Director of the Federal Register 
as of February 13, 2004.
    The incorporation by reference of certain other publications, as 
listed in the regulations, was approved previously by the Director of 
the Federal Register as of February 17, 1998 (63 FR 1905, January 13, 
1998).

ADDRESSES: The service information referenced in this AD may be 
obtained from Airbus, 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: Tim Dulin, Aerospace Engineer,

[[Page 1510]]

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) by superseding AD 98-01-12, 
amendment 39-10275 (63 FR 1905, January 13, 1998), which is applicable 
to certain Airbus Model A320 series airplanes, was published in the 
Federal Register on November 4, 2003 (68 FR 62405). The action proposed 
to continue to require an inspection to detect moisture and migrated 
bushings of the guide fittings of the safety locking pins of the 
passenger doors, removal of any moisture, application of grease, and 
reinstallation of any migrated bushing. That action also proposed to 
continue to require installation of a greasing nipple on the guide 
fitting of the locking pin and on three telescopic rods on the 
passenger doors. The new action proposed to add a requirement for 
modification of the upper guide fitting of the locking pin, and expand 
the applicability in the existing AD.

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

    There are approximately 168 airplanes of U.S. registry that will be 
affected by this AD.
    The actions that are currently required by AD 98-01-12 take about 4 
work hours per airplane (1 work hour per door) to accomplish, at an 
average labor rate of $65 per work hour. Based on these figures, the 
cost impact of the currently required actions is estimated to be $260 
per airplane.
    The new modification that is required by this AD action will take 
about 8 work hours per airplane (2 work hours per door) to accomplish, 
at an average labor rate of $65 per work hour. Required parts costs 
will be minimal. Based on these figures, the cost impact of the 
modification required by this AD on U.S. operators is estimated to be 
$87,360, or $520 per airplane.
    The cost impact figures discussed above are 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 ``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 removing amendment 39-10275 (63 FR 1905, 
January 13, 1998), and by adding a new airworthiness directive (AD), 
amendment 39-13416, to read as follows:

2004-01-03 Airbus: Amendment 39-13416. Docket 2001-NM-120-AD. 
Supersedes AD 98-01-12, Amendment 39-10275.

    Applicability: Model A319, A320, and A321 series airplanes; 
certificated in any category; except those on which Airbus 
Modification 27142 has been incorporated during production.
    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent jamming of the locking pin of the passenger door, 
which could result in inability to open the passenger door and delay 
of evacuation in an emergency, resulting in possible injury to 
passengers or crew; accomplish the following:

Restatement of Requirements of AD 98-01-12

Inspection/Corrective Action

    (a) Prior to the accumulation of 450 hours, time-in-service 
after one year from the delivery date of the airplane, or within 450 
hours, time-in-service after February 17, 1998 (the effective date 
of AD 98-01-12, amendment 39-10275), whichever occurs later; perform 
an inspection to detect moisture or migrated bushings of the guide 
fittings of the upper safety locking pins on each passenger door, in 
accordance with Airbus Industrie All Operators Telex (AOT) 52-06, 
dated February 4, 1994.
    (1) If any moisture is found in the guide fitting, prior to 
further flight, remove the moisture, dry the guide fitting, fill it 
with low temperature grease, and reinstall the guide fitting with 
bolts, washers, and nuts in accordance with the AOT.
    (2) If any migrated bushing is found, prior to further flight, 
reinstall the bushing using Loctite 672 in accordance with the AOT. 
If the bushing cannot be reinstalled prior to further flight, the 
airplane may be operated without the upper locking pin for an 
additional 50 hours time-in-service or three days after 
accomplishing the inspection, whichever occurs first, provided that 
the requirements specified in paragraphs (a)(2)(i), (a)(2)(ii), and 
(a)(2)(iii) of this AD are accomplished. This compliance time 
applies to each passenger door.
    (i) The connecting rod to the locking shaft shall be removed.
    (ii) The guide fitting shall remain installed.
    (iii) The cavity in the guide fitting (which results from the 
removal of the upper locking pin) shall be covered with high speed 
tape to prevent moisture ingress.

Installation of Greasing Nipple

    (b) Within 15 months after February 17, 1998, install a greasing 
nipple on the guide fitting of the locking pin and on three 
telescopic rods on the passenger doors in accordance with Airbus 
Industrie Service Bulletin No. A320-52-1057, dated July 26, 1994.

New Requirements of This AD

Modification

    (c) Modify the upper guide fitting of the locking pin in 
accordance with paragraphs 3.A. through 3.D. of the Accomplishment 
Instructions of Airbus Service Bulletin A320-52-1105, Revision 02, 
dated May 21, 2002; at

[[Page 1511]]

the time specified in paragraph (c)(1) or (c)(2) of this AD, as 
applicable. Accomplishment of the modification before the effective 
date of this AD in accordance with Airbus Service Bulletin A320-52-
1105, dated September 29, 2000; or Revision 01, dated August 7, 
2001; is considered acceptable for compliance with the corresponding 
action in this paragraph.
    (1) For Model A320 and A321 series airplanes on which Airbus 
Service Bulletin A320-52-1057 has been incorporated in service: 
Within 1 year after the effective date of this AD.
    (2) For Model A319, A320, and A321 series airplanes on which 
Airbus Modification 24389 was done in production: Within 3 years 
after the effective date of this AD.

Alternative Methods of Compliance

    (d)(1) 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.
    (2) Alternative methods of compliance, approved previously per 
AD 98-01-12, amendment 39-10275, are approved as alternative methods 
of compliance with paragraphs (a) and (b) of this AD, as applicable.

Incorporation by Reference

    (e) The actions shall be done in accordance with Airbus 
Industrie All Operators Telex (AOT) 52-06, dated February 4, 1994; 
Airbus Industrie Service Bulletin No. A320-52-1057, dated July 26, 
1994; and Airbus Service Bulletin A320-52-1105, Revision 02, dated 
May 21, 2002; as applicable.
    (1) The incorporation by reference of Airbus Service Bulletin 
A320-52-1105, Revision 02, dated May 21, 2002, is approved by the 
Director of the Federal Register in accordance with 5 U.S.C. 552(a) 
and 1 CFR part 51.
    (2) The incorporation by reference of Airbus Industrie All 
Operators Telex (AOT) 52-06, dated February 4, 1994; and Airbus 
Industrie Service Bulletin No. A320-52-1057, dated July 26, 1994; 
was approved previously by the Director of the Federal Register as 
of February 17, 1998 (63 FR 1905, January 13, 1998).
    (3) Copies may be obtained from Airbus, 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 1: The subject of this AD is addressed in French 
airworthiness directive 2001-100(B), dated March 21, 2001.

Effective Date

    (f) This amendment becomes effective on February 13, 2004.

    Issued in Renton, Washington, on December 29, 2003.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 04-123 Filed 1-8-04; 8:45 am]
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