[Federal Register: January 9, 2004 (Volume 69, Number 6)]
[Rules and Regulations]
[Page 1509-1511]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr09ja04-5]
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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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