[Federal Register Volume 62, Number 37 (Tuesday, February 25, 1997)]
[Proposed Rules]
[Pages 8408-8410]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-4556]


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Proposed Rules
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains notices to the public of 
the proposed issuance of rules and regulations. The purpose of these 
notices is to give interested persons an opportunity to participate in 
the rule making prior to the adoption of the final rules.

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Federal Register / Vol. 62, No. 37 / Tuesday, February 25, 1997 / 
Proposed Rules

[[Page 8408]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 94-NM-94-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A320 and Model A321 Series 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Supplemental notice of proposed rulemaking; reopening of 
comment period.

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SUMMARY: This document revises an earlier proposed airworthiness 
directive (AD), applicable to certain Airbus Model A320 series 
airplanes, that would have required repetitive inspections to verify 
proper installation of the plain bushings of the upper and lower 
connection links on the forward and aft passenger/crew doors, and 
correction of discrepancies. That AD also would have required 
replacement of the shouldered bushing on the locking mechanism with a 
new oversized bushing, which would have terminated the repetitive 
inspection requirements. That proposal was prompted by a report that, 
during an emergency evacuation of in-service airplanes, the left aft 
passenger/crew door jammed against the fuselage structure in a nearly 
closed position due to bushing migration. This action revises the 
proposed rule by expanding the applicability of the proposed rule to 
include additional airplanes; and adding new repetitive inspections and 
a terminating modification for those new airplanes. The actions 
specified by this proposed AD are intended to prevent jamming of the 
passenger/crew door, which could delay or impede the evacuation of 
passengers during an emergency.

DATES: Comments must be received by March 17, 1997.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-103, 
Attention: Rules Docket No. 94-NM-94-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.
    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: Charles Huber, Aerospace Engineer, 
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206) 
227-2141; fax (206) 227-1100.

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 notice may be changed in 
light of the comments received.
    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 notice must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 94-NM-94-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-103, Attention: Rules 
Docket No. 94-NM-94-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    A proposal to amend part 39 of the Federal Aviation Regulations (14 
CFR part 39) to add an airworthiness directive (AD), applicable to 
certain Airbus Model A320 and Model A320 series airplanes, was 
published as a notice of proposed rulemaking (NPRM) in the Federal 
Register on August 30, 1994 (59 FR 44670). That NPRM would have 
required repetitive detailed visual inspections to verify proper 
installation of the plain bushings of the upper and lower connection 
links on the forward and aft passenger/crew doors, and correction of 
discrepancies. That NPRM also would have required replacement of the 
shouldered bushing on the locking mechanism with a new oversized 
bushing, which would have terminated the repetitive inspection 
requirements. That NPRM was prompted by a report that, during an 
emergency evacuation of in-service airplanes, the left aft passenger/
crew door jammed against the fuselage structure in a nearly closed 
position due to bushing migration. That condition, if not corrected, 
could delay or impede the evacuation of passengers during an emergency.

Actions Prompting This Supplemental Proposal

    Several commenters who responded to the original notice pointed out 
that the applicability of the proposed AD should be revised to include 
Airbus Model A320 and Model A321 series airplanes, on which Airbus 
Modification 22422 (reference Airbus Service Bulletin A320-52-1027) was 
installed during production. The unsafe condition (i.e., bushing 
migration) addressed by the proposal has also occurred on these 
airplanes, and Airbus has issued service information that contains new 
procedures for addressing the unsafe condition on these airplanes.

Explanation of New Relevant Service Information

    Since issuance of the NPRM, Airbus has issued All Operators Telex 
(AOT)

[[Page 8409]]

52-07, dated July 28, 1994, and Service Bulletin A320-52-1066, dated 
March 6, 1995. These service documents describe procedures for 
performing repetitive detailed visual inspections to verify proper 
installation of the plain bushings of the upper and lower connection 
links.
    Airbus also has issued Service Bulletin A320-52-1064, Revision 1, 
dated September 8, 1995, which describes procedures for modification of 
the frame segment bushings. The modification involves replacing the 
plain bushing with a shouldered bushing on the frame used for 
attachment of the connection links. Accomplishment of the modification 
would eliminate the need for the repetitive detailed visual 
inspections.
    The effectivity listing of these service documents includes certain 
additional Airbus Model A320 and Model A321 series airplanes that are 
subject to the unsafe condition. (These airplanes were not identified 
in the applicability of the original NPRM.)
    The Direction Generale de l'Aviation Civile (DGAC), which the 
airworthiness authority for France, classified these service documents 
as mandatory and issued French airworthiness directive 95-004-062(B)R1, 
dated May 10, 1995, in order to assure the continued airworthiness of 
these airplanes in France.

FAA's Action

    In light of this new information, the FAA has revised the 
applicability of the proposal to include the additional airplanes 
listed in the new Airbus service documents. For these additional 
airplanes, the FAA also has revised the proposal to include new 
requirements for accomplishing the procedures specified in those 
service bulletins. The actions that were proposed in the originally-
issued NPRM for the other affected airplanes are retained in this 
supplemental NPRM.
    In addition, the FAA has increased the labor rate used in the cost 
impact calculations, below, from $55 per work hour to $60 per work 
hour. The $60 figure more accurately represents the current labor rate 
in the aviation industry.

Conclusion

    Since these changes expand the scope of the originally proposed 
rule, the FAA has determined that it is necessary to reopen the comment 
period to provide additional opportunity for public comment.

Cost Impact

    The FAA estimates that 94 Airbus Model A320 and Model A321 series 
airplanes of U.S. registry would be affected by this proposed AD.
    It would take approximately 6 work hours per airplane to accomplish 
the proposed detailed visual inspection, at an average labor rate of 
$60 per work hour. Based on these figures, the cost impact of the 
modification proposed AD on U.S. operators is estimated to be $33,840, 
or $360 per airplane, per inspection cycle.
    For certain airplanes, it would take approximately 72 work hours 
per airplane to accomplish the proposed modification, at an average 
labor rate of $60 per work hour. Required parts would be supplied by 
the manufacturer at no cost to the operators. Based on these figures, 
the cost impact of the modification proposed AD on U.S. operators is 
estimated to be $406,080, or $4,320 per airplane.
    For certain other airplanes, it would take approximately 53 work 
hours per airplane to accomplish the proposed modification, at an 
average labor rate of $60 per work hour. Required parts would be 
supplied by the manufacturer at no cost to the operators. Based on 
these figures, the cost impact of the modification proposed AD on U.S. 
operators is estimated to be $298,920, or $3,180 per airplane.
    The cost impact figures discussed above are 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 AD were not adopted.

Regulatory Impact

    The regulations proposed herein would not have substantial direct 
effects 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, in 
accordance with Executive Order 12612, it is determined that this 
proposal would not have sufficient federalism implications to warrant 
the preparation of a Federalism Assessment.
    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 94-NM-94-AD.

    Applicability: Model A320 and Model A321 series airplanes; on 
which Airbus Modification 22422 (reference Airbus Service Bulletin 
A320-52-1027) has been installed, or Airbus Modification 24497 
(reference Airbus Service Bulletin A320-52-1064) has not been 
installed; 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 (e) 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 jamming of the passenger/crew door, which could delay 
or impede the evacuation of passengers during an emergency, 
accomplish the following:
    (a) For Model A320 series airplanes on which Airbus Modification 
22422 (reference Airbus Service Bulletin A320-52-1027) has not been 
accomplished: Within 450 flight hours after the effective date of 
this AD, perform a detailed visual inspection to verify proper 
installation of the plain bushings of the upper and lower connection 
links on the forward and aft passenger/crew doors, in

[[Page 8410]]

accordance with Airbus Service Bulletin A320-52-1047, dated April 
25, 1994.
    (1) If all bushings are installed properly, repeat the 
inspection thereafter at intervals not to exceed 900 flight hours 
until the modification required by paragraph (c) of this AD is 
accomplished.
    (2) If any bushing has migrated, prior to further flight, remove 
the passenger/crew door and visually inspect the bushing to detect 
damage, in accordance with the service bulletin.
    (i) If the bushing housings are not damaged, prior to further 
flight, reinstall the bushing in accordance with the service 
bulletin. Repeat the detailed visual inspections of the bushings 
thereafter at intervals not to exceed 450 flight hours until the 
modification required by paragraph (b) of this AD is accomplished.
    (ii) If any bushing housing is damaged, prior to further flight, 
ream the door structure and install an oversize shouldered bushing, 
in accordance with the service bulletin. If the damage is not 
completely removed after reaming, prior to further flight, repair 
the bushing housing in accordance with a method approved by the 
Manager, Standardization Branch, ANM-113, FAA, Transport Airplane 
Directorate.
    (b) For Model A320 and Model A321 series airplanes; on which 
Airbus Modification 22422 (reference Airbus Service Bulletin A320-
52-1027) has been installed, and Airbus Modification 24497 
(reference Airbus Service Bulletin A320-52-1064) has not been 
installed: Within 450 flight hours after the effective date of this 
AD, perform a detailed visual inspection to verify proper 
installation of the plain bushings of the upper and lower connection 
links (2 bushings per door), in accordance with Airbus All Operators 
Telex AOT 52-07, dated July 28, 1994, or Airbus Service Bulletin 
A320-52-1066, dated March 6, 1995.
    (1) If the bushings are installed properly, repeat the detailed 
visual inspection thereafter at intervals not to exceed 900 flight 
hours.
    (2) If any bushing is found to be improperly installed, prior to 
further flight, modify the frame segment bushings in accordance with 
Airbus Service Bulletin A320-52-1064, Revision 1, dated September 8, 
1995. Accomplishment of the modification constitutes terminating 
action for the requirements of this AD.
    (c) For Model A320 series airplanes on which Airbus Modification 
22422 (reference Airbus Service Bulletin A320-52-1027) has not been 
accomplished: Within 3,500 flight hours after the effective date of 
this AD, replace the shouldered bushing on the locking mechanism 
with a new oversized bushing (Kit No. 521027A02), in accordance with 
Airbus Service Bulletin A320-52-1027, Revision 2, dated February 18, 
1993, or Revision 3, dated December 10, 1993. Accomplishment of this 
modification constitutes terminating action for the repetitive 
inspection requirements of paragraph (a) of this AD.
    (d) For Model A320 and Model A321 series airplanes on which 
Airbus Modification 22422 (reference Airbus Service Bulletin A320-
52-1027) has been installed, and Airbus Modification 24497 
(reference Airbus Service Bulletin A320-52-1064) has not been 
installed: Within 15 months after the effective date of this AD, 
modify the frame segment bushing in accordance with Airbus Service 
Bulletin A320-52-1064, Revision 1, dated September 8, 1995. 
Accomplishment of the modification constitutes terminating action 
for the repetitive detailed visual inspection requirements of 
paragraph (b) of this AD.
    (e) 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, Standardization Branch, ANM-113, 
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, 
Standardization Branch, ANM-113.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Standardization Branch, ANM-113.

    (f) 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.

    Issued in Renton, Washington, on February 19, 1997.
James V. Devany,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 97-4556 Filed 2-24-97; 8:45 am]
BILLING CODE 4910-13-U