[Federal Register Volume 66, Number 159 (Thursday, August 16, 2001)]
[Rules and Regulations]
[Pages 42939-42941]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-20590]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-138-AD; Amendment 39-12383; AD 2001-16-14]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
is applicable to certain Airbus Model A319, A320, and A321 series 
airplanes. This action requires modification of the telescopic girt bar 
of the escape slide/raft assembly, and follow-on actions. This action 
is necessary to prevent failure of the escape slide/raft to deploy 
correctly, which could result in the slide being unusable during an 
emergency evacuation and consequent injury to passengers or airplane 
crewmembers. This action is intended to address the identified unsafe 
condition.

DATES: Effective August 31, 2001.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of August 31, 2001.
    Comments for inclusion in the Rules Docket must be received on or 
before September 17, 2001.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2001-NM-138-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9:00 a.m. and 3:00 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 the Internet must contain 
``Docket No. 2001-NM-138-AD'' in the subject line and need not be 
submitted in triplicate. Comments sent via fax or the Internet as 
attached electronic files must be formatted in Microsoft Word 97 for 
Windows or ASCII text.
    The service information referenced in this AD may be obtained from 
Airbus Industrie, Customer Services Directorate, 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; 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: 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 there have been 
several reports of the telescopic girt bar of the slide/raft assembly 
detaching from the door sill fittings and preventing proper deployment 
of the emergency escape slide. The telescopic girt bar is designed to 
be retractable and removable from the door sill to ensure the raft is 
accessible in an emergency evacuation. The telescopic girt bar is 
normally locked in an extended position by a trigger mechanism that 
prevents retraction unless pulled. Investigation of the affected girt 
bars revealed that the trigger mechanism was not operational due to an 
incorrectly machined chamfer of the girt bar, which allowed the 
mechanism to retract and detach from the door sill when opening the 
door. Such conditions, if not corrected, could result in failure of the 
escape slide/raft to deploy correctly, which could result in the slide 
being unusable during an emergency evacuation and consequent injury to 
passengers or airplane crewmembers.
    Following the incidents previously described, Airbus Industrie 
issued All Operators Telex A320-52A1110, dated April 11, 2001, to 
address the identified unsafe condition. However, one report was 
received that, during accomplishment of the functional test specified 
in that AOT, an operator did the scheduled slide deployment and the 
girt bar detached from the door sill. Investigation revealed that the 
chamfer was slightly out of tolerance and damage was found in the area 
of the trigger lever. The girt bar trigger end deviated from the 
production drawing and the deviation was not identified until after the 
AOT had been issued. Subsequently, it has been determined that the 
actions specified in that AOT are not sufficient to identify all 
defective girt bars, and a new AOT has been issued.

Explanation of Relevant Service Information

    Airbus Industrie has issued AOT A320-52A1111, Revision 01, dated 
July 23, 2001, including Technical Disposition 959.1492/01, Issue C, 
dated July 17, 2001; which describes procedures for modification of the 
telescopic girt bar of the escape slide/raft assembly, and follow-on 
actions. The modification consists of rework of the trigger end of the 
telescopic girt bar, and installation of a U-shaped reinforcement 
section on the bar. The follow-on actions include repetitive 
inspections of the telescopic girt bar for discrepancies (damage or 
corrosion), and functional tests of the telescopic girt bar to ensure 
it does not retract when a measured force (34 to 45 pounds) is applied. 
If discrepancies are found, the service bulletin describes procedures 
for replacement of the U-shaped section or rivets with new parts.
    The DGAC classified AOT A320-52A1111, dated July 5, 2001, as 
mandatory and issued French airworthiness directive 2001-275(B), dated 
July 11, 2001, in order to assure the continued airworthiness of these 
airplanes in France.

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 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 Rule

    Since an unsafe condition has been identified that is likely to 
exist or

[[Page 42940]]

develop on other airplanes of the same type design registered in the 
United States, this AD is being issued to prevent failure of the escape 
slide/raft to deploy correctly, which could result in the slide being 
unusable during an emergency evacuation and consequent injury to 
passengers or airplane crewmembers. This AD requires modification of 
the telescopic girt bar of the escape slide/raft assembly, and follow-
on actions. The actions are required to be accomplished in accordance 
with the AOT described previously, except as discussed below.

Differences Between This AD and the AOT

    The AOT specifies performing a ``visual inspection'' of the U-
shaped section and rivet heads of the girt bar within 18 months after 
the modification, and repeat the inspection at intervals not to exceed 
18 months. As the compliance time would allow opportunity for public 
comment, the FAA may consider additional rulemaking to require these 
inspections.
    Additionally, the AOT does not describe procedures for corrective 
action if the telescopic girt bar retracts when performing the 
functional test; however, this AD requires replacement of any 
discrepant parts with new parts and accomplishment of another 
functional test after replacement of the parts to ensure the girt bar 
does not retract.

Interim Action

    This is interim action. The manufacturer has advised that a new 
modification is currently being developed that will positively address 
the unsafe condition addressed by this AD. Once that modification is 
developed, approved, and available, the FAA may consider additional 
rulemaking.

Determination of Rule's Effective Date

    Since a situation exists that requires the immediate adoption of 
this regulation, it is found that notice and opportunity for prior 
public comment hereon are impracticable, and that good cause exists for 
making this amendment effective in less than 30 days.

Comments Invited

    Although this action is in the form of a final rule that involves 
requirements affecting flight safety and, thus, was not preceded by 
notice and an opportunity for public comment, comments are invited on 
this rule. Interested persons are invited to comment on this 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 under the caption ``ADDRESSES.'' 
All communications received on or before the closing date for comments 
will be considered, and this rule may be amended in light of the 
comments received. Factual information that supports the commenter's 
ideas and suggestions is extremely helpful in evaluating the 
effectiveness of the AD action and determining whether additional 
rulemaking action would be needed.
    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 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 rule that might 
suggest a need to modify the 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 that 
summarizes each FAA-public contact concerned with the substance of this 
AD will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this rule must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2001-NM-138-AD.'' The postcard will be date stamped 
and returned to the commenter.

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.
    The FAA has determined that this regulation is an emergency 
regulation that must be issued immediately to correct an unsafe 
condition in aircraft, and that it is not a ``significant regulatory 
action'' under Executive Order 12866. It has been determined further 
that this action involves an emergency regulation under DOT Regulatory 
Policies and Procedures (44 FR 11034, February 26, 1979). If it is 
determined that this emergency regulation otherwise would be 
significant under DOT Regulatory Policies and Procedures, a final 
regulatory evaluation will be prepared and placed in the Rules Docket. 
A copy of it, if filed, 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:

2001-16-14 Airbus Industrie: Amendment 39-12383. Docket 2001-NM-138-
AD.

    Applicability: Model A319, A320, and A321 series airplanes 
equipped with telescopic girt bars of the escape slide/raft 
assembly, as listed in Airbus Industrie All Operators Telex (AOT) 
A320-52A1111, Revision 01, dated July 23, 2001; certificated in any 
category.


    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
otherwise 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 (b) 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 failure of the escape slide/raft to deploy correctly, 
which could result in the slide being unusable during an emergency 
evacuation and consequent injury to passengers or airplane 
crewmembers, accomplish the following:

[[Page 42941]]

Modification/Follow-On Actions

    (a) Within 1,500 flight hours after the effective date of this 
AD: Modify the telescopic girt bar of the escape slide/raft assembly 
installed on all passenger and crew doors and do a functional test 
to ensure the girt bar does not retract, per Airbus Industrie AOT 
A320-52A1111, Revision 01, dated July 23, 2001.
    (1) If the girt bar retracts, before further flight, replace any 
discrepant parts and do another functional test to ensure the girt 
bar does not retract, per the AOT. Repeat the functional test after 
that at intervals not to exceed 18 months.
    (2) If the girt bar does not retract, repeat the functional test 
as required by paragraph (a)(1) of this AD.

    Note 2:  Modification and follow-on actions accomplished prior 
to the effective date of this AD per Airbus Industrie AOT A320-
52A1111, dated July 5, 2001, are considered acceptable for 
compliance with the applicable actions specified in this amendment.

Alternative Methods of Compliance

    (b) 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, FAA, 
Transport Airplane Directorate. 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 3:  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

    (c) 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

    (d) The actions shall be done in accordance with Airbus 
Industrie All Operators Telex A320-52A1111, Revision 01, dated July 
23, 2001, including Airbus Industrie Technical Disposition 959.1492/
01, Issue C, dated July 17, 2001. All Operators Telex A320-52A1111 
contains the following list of effective pages:

------------------------------------------------------------------------
                                   Revision
          Page number             level shown      Date shown on page
                                    on page
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1-4............................  01            July 23, 2001.
 
                    Technical Disposition 959.1492/01
 
1-4............................  C             July 17, 2001.
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    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 4:  The subject of this AD is addressed in French 
airworthiness directive 2001-275(B) dated July 11, 2001.

Effective Date

    (e) This amendment becomes effective on August 31, 2001.

    Issued in Renton, Washington, on August 9, 2001.
Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-20590 Filed 8-15-01; 8:45 am]
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