[Federal Register Volume 66, Number 170 (Friday, August 31, 2001)]
[Proposed Rules]
[Pages 45950-45951]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-21974]



[[Page 45950]]

-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-71-AD]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: This document proposes the adoption of a new airworthiness 
directive (AD) that is applicable to certain Airbus Model A319, A320, 
and A321 series airplanes. This proposal would require 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: Comments must be received by October 1, 2001.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2001-NM-71-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9 a.m. and 3 p.m., Monday through Friday, except 
Federal holidays. Comments may be submitted via fax to (425) 227-1232. 
Comments may also be sent via the Internet using the following address: 
[email protected]. Comments sent via fax or the Internet must 
contain ``Docket Number 2001-NM-71-AD'' in the subject line and need 
not be submitted in triplicate. Comments sent via the Internet as 
attached electronic files must be formatted in Microsoft Word 97 for 
Windows or ASCII text.
    The service information referenced in the proposed rule may be 
obtained from Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 
Blagnac Cedex, France. This information may be examined at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington.

FOR FURTHER INFORMATION CONTACT: Tamra Elkins, Aerospace Engineer, 
International Branch, FAA, Transport Airplane Directorate, 1601 Lind 
Avenue, SW., Renton, Washington, telephone (425) 227-2669, fax (425) 
227-1149.

SUPPLEMENTARY INFORMATION:

Comments Invited

    Interested persons are invited to participate in the making of the 
proposed rule by submitting such written data, views, or arguments as 
they may desire. Communications shall identify the Rules Docket number 
and be submitted in triplicate to the address specified above. All 
communications received on or before the closing date for comments, 
specified above, will be considered before taking action on the 
proposed rule. The proposals contained in this action may be changed in 
light of the comments received.
    Submit comments using the following format:
     Organize comments issue-by-issue. For example, discuss a 
request to change the compliance time and a request to change the 
service bulletin reference as two separate issues.
     For each issue, state what specific change to the proposed 
AD is being requested.
     Include justification (e.g., reasons or data) for each 
request.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the proposed rule. All 
comments submitted will be available, both before and after the closing 
date for comments, in the Rules Docket for examination by interested 
persons. A report summarizing each FAA-public contact concerned with 
the substance of this proposal will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this action must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2001-NM-71-AD.'' The postcard will be date stamped and 
returned to the commenter.

Availability of NPRMs

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, Transport Airplane Directorate, ANM-114, Attention: Rules 
Docket No. 2001-NM-71-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    The Direction Generale de l'Aviation Civile (DGAC), which is the 
airworthiness authority for France, notified the FAA that an unsafe 
condition may exist on certain Airbus Model A319, A320, and A321 series 
airplanes. The DGAC advises that, during deployment tests of the escape 
slide, in two cases the slide bar detached from the door sill and the 
escape slide failed to inflate. It was found that the carbon-steel 
trigger spring was ruptured due to severe corrosion. The function of 
the trigger spring is to hold the trigger in a certain position to 
mechanically secure the telescopic slide bar in the extended position. 
If the trigger spring ruptures, the slide bar may be unlocked and then 
held in an extended position only by two internal springs. This 
condition, if not corrected, 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.

Explanation of Relevant Service Information

    Airbus has issued Service Bulletin A320-52-1102, Revision 01, dated 
November 25, 1999, which describes procedures for replacement of the 
carbon-steel slide bar trigger spring with a stainless steel spring. 
Accomplishment of the action specified in the service bulletin is 
intended to adequately address the identified unsafe condition. The 
DGAC classified this service bulletin as mandatory and issued French 
airworthiness directive 2001-063(B), dated February 21, 2001, in order 
to assure the continued airworthiness of these airplanes in France.

Difference Between Proposed Rule and Service Bulletin

    Airbus Service Bulletin A320-52-1102, Revision 01, dated November 
25, 1999, specifies that Airbus Service Bulletin A320-52-1068 is to be 
accomplished concurrently. However, French airworthiness directive 
2001-063(B), dated February 21, 2001, provides that simultaneous (or 
concurrent) accomplishment of Airbus Service Bulletin A320-52-1068 is 
not required. Similarly, this proposed rule would not require 
concurrent accomplishment of Airbus Service Bulletin A320-52-1068.

FAA's Conclusions

    These airplane models are manufactured in France and are type 
certificated for operation in the United States under the provisions of 
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and 
the applicable bilateral airworthiness agreement. Pursuant to this 
bilateral airworthiness agreement, the DGAC has kept the FAA informed 
of the situation

[[Page 45951]]

described above. The FAA has examined the findings of the DGAC, 
reviewed all available information, and determined that AD action is 
necessary for products of this type design that are certificated for 
operation in the United States.

Explanation of Requirements of Proposed Rule

    Since an unsafe condition has been identified that is likely to 
exist or develop on other airplanes of the same type design registered 
in the United States, the proposed AD would require accomplishment of 
the actions specified in the service bulletin described previously.

Cost Impact

    The FAA estimates that 152 airplanes of U.S. registry would be 
affected by this proposed AD, that it would take approximately 8 work 
hours per airplane to accomplish the proposed 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 the proposed 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 proposed requirements of 
this AD action, and that no operator would accomplish those actions in 
the future if this proposed 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 proposed herein would 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 proposal would not have federalism implications 
under Executive Order 13132.
    For the reasons discussed above, I certify that this proposed 
regulation (1) is not a ``significant regulatory action'' under 
Executive Order 12866; (2) is not a ``significant rule'' under the DOT 
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 
and (3) if promulgated, 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 copy of the draft 
regulatory evaluation prepared for this action is contained in the 
Rules Docket. A copy of it may be obtained by contacting the Rules 
Docket at the location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 
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:

Airbus Industrie: Docket 2001-NM-71-AD.

    Applicability: Model A319, A320, and A321 series airplanes, all 
serial numbers having received Airbus Modification 20234 
(installation of telescopic girt bar for slide raft) or Airbus 
Service Bulletin A320-25-1055 without Airbus Modification 28212 in 
production or Airbus Service Bulletin A320-52-1102, Revision 01, 
dated November 25, 1999, in service; 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 from 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 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.

    Note 3: The subject of this AD is addressed in French 
airworthiness directive 2001-063(B), dated February 21, 2001.


    Issued in Renton, Washington, on August 24, 2001.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-21974 Filed 8-30-01; 8:45 am]
BILLING CODE 4910-13-P