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

[Federal Register Volume 67, Number 20 (Wednesday, January 30, 2002)]
[Rules and Regulations]
[Pages 4333-4335]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-1817]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-71-AD; Amendment 39-12612; AD 2002-01-18]
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 adopts a new airworthiness directive (AD), 
applicable to certain Airbus Model A319, A320, and A321 series 
airplanes, that requires replacement of the trigger spring of the slide 
bar on each of the passenger doors with a new, stronger trigger spring. 
This action is necessary to prevent corrosion of the trigger spring on 
the slide bar of the passenger doors, which could result in incorrect 
locking of the slide bar and, during deployment of the escape slide, 
lead to a delay in evacuating passengers in an emergency. This action 
is intended to address the identified unsafe condition.

DATES: Effective March 6, 2002.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of March 6, 2002.

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: Dan Rodina, Aerospace Engineer, 
International Branch, FAA, Transport

[[Page 4334]]

Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington, 
telephone (425) 227-2125, 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, A320, 
and A321 series airplanes was published in the Federal Register on 
August 31, 2001 (66 FR 45950). That action proposed to require 
replacement of the trigger spring of the slide bar on each of the 
passenger doors with a new, stronger trigger spring.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the single comment received.

Request To Revise Proposed Compliance Time

    The commenter requests that the FAA revise the compliance time of 
paragraph (a) of the proposed AD to refer to ``30 months after the 
`entry in service' of the airplane'' instead of ``30 months from the 
date of manufacture of the airplane.'' The commenter points out that 
the date of manufacture is the date of the first flight of the 
airplane, whereas the date of ``entry into service'' is the date of 
delivery of the airplane. The difference between these dates could be 
one month or more. The commenter notes that its recommended change 
would make the FAA's proposed AD consistent with the corresponding 
French AD.
    We do not concur. For clarification, we define the ``date of 
manufacture'' as the date of issuance of the Certificate of 
Airworthiness. We find that this constitutes a definitive date when all 
of the manufacturing processes are completed. We have determined that 
this date should be readily discernible by operators, and no change to 
the final rule is necessary in this regard.

Explanation of Change to Applicability Statement

    The FAA has determined that the wording of the applicability 
statement in the proposed AD may be confusing for some operators. 
Therefore, we have revised the wording of the applicability statement 
of this final rule for clarity.

Conclusion

    After careful review of the available data, including the comment 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule with the change described 
previously. The FAA has determined that this change will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.

Cost Impact

    The FAA estimates that 152 Model A319, A320, and A321 series 
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 
replacement, and that the average labor rate is $60 per work hour. 
Required parts will be provided at no charge by the manufacturer. Based 
on these figures, the cost impact of this AD on U.S. operators is 
estimated to be $72,960, or $480 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 ``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

    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:

2002-01-18  Airbus Industrie: Amendment 39-12612. Docket 2001-NM-71-
AD.

    Applicability: Model A319, A320, and A321 series airplanes; all 
serial numbers having received Airbus Modification 20234 (Airbus 
Service Bulletin A320-25-1055) (installation of telescopic girt bar 
for slide raft), but NOT having received Airbus Modification 28212 
(Airbus Service Bulletin A320-52-1102, Revision 01, dated November 
25, 1999); 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 (c) 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 corrosion of the trigger spring on the slide bar of 
the forward and aft passenger doors, which could result in incorrect 
locking of the slide bar during deployment of the escape slide and 
lead to a delay in evacuating passengers in an emergency, accomplish 
the following:

Replacement

    (a) Within 18 months of the effective date of this AD or within 
30 months after the date of manufacture of the airplane, whichever 
occurs later: Replace the carbon-steel trigger spring having part 
number (P/N) D5211046420000 on each of the forward and aft passenger 
doors with a stainless steel trigger spring having P/N 
D5211046420200, in accordance with Airbus Service Bulletin A320-52-
1102, Revision 01, dated November 25, 1999.

Spares

    (b) As of the effective date of this AD, no person shall install 
a carbon-steel trigger

[[Page 4335]]

spring having P/N D5211046420000, on any airplane.

Alternative Methods of Compliance

    (c) 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, 
Transport Airplane Directorate, FAA. 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 Manager, International Branch, ANM-116.

Special Flight Permits

    (d) 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.

Incorporation by Reference

    (e) The actions shall be done in accordance with Airbus Service 
Bulletin A320-52-1102, Revision 01, dated November 25, 1999. 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 2001-063(B), dated February 21, 2001.

Effective Date

    (f) This amendment becomes effective on March 6, 2002.

    Issued in Renton, Washington, on January 17, 2002.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 02-1817 Filed 1-29-02; 8:45 am]
BILLING CODE 4910-13-U

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