Airworthiness Directives; Airbus Model A320 and Model A321 Series Airplanes

[Federal Register Volume 63, Number 136 (Thursday, July 16, 1998)]
[Rules and Regulations]
[Pages 38293-38295]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-18768]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 94-NM-94-AD; Amendment 39-10657; AD 98-15-06]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A320 and Model 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 A320 and Model A321 series 
airplanes, that requires 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. This amendment also requires installation of shouldered 
bushings on the frame segment used for attachment of the connection 
links or modification of the frame segment bushing (as applicable), 
which terminates the repetitive inspection requirements. This amendment 
is 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. The actions specified by this AD are intended to prevent 
jamming of the passenger/crew door, which could delay or impede the 
evacuation of passengers during an emergency.

DATES: Effective August 20, 1998.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of August 20, 1998.

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: Norman B. Martenson, Manager, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2110; 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 A320 and A321 
series airplanes was published as a supplemental notice of proposed 
rulemaking (NPRM) in the Federal Register on February 25, 1997 (62 FR 
8408). That action proposed to require 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 action also proposed to require 
replacement of the shouldered bushing on the locking mechanism with a 
new oversized bushing or modification of the frame segment bushing (as 
applicable), which terminates the repetitive inspection requirements.

Comments

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

Request to Revise Applicability

    One commenter, Airbus, requests that the applicability of the 
supplemental NPRM be revised to specify that the AD applies to (1) 
airplanes on which Airbus Modification 24497 has not been installed in 
production; and (2) airplanes on which Airbus Service Bulletin A320-52-
1027, Revision 2, dated February 18, 1993, Revision 3, dated December 
10, 1993, or Airbus Service Bulletin A320-52-1064, Revision 1, dated 
September 8, 1995, has not been installed.
    Airbus advises that installation of Airbus Modification 22422 in 
production is not equivalent to accomplishment of Airbus Service 
Bulletin A320-52-1027. (The applicability of the supplemental NPRM 
incorrectly equates Modification 22422 to Airbus Service Bulletin A320-
52-1027.) The commenter adds that airplanes on which Airbus Service 
Bulletin A320-52-1027 has been accomplished are not affected by the 
requirements of the supplemental NPRM. The commenter states further 
that Airbus Service Bulletin A320-52-1064 must be accomplished on 
airplanes on which Airbus Modification 22422 was installed in 
production.
    The FAA concurs with the commenter's request. Installation of 
shouldered bushings on the segment frame is necessary in order to 
provide a full solution and adequately address the identified unsafe 
condition. Airbus Modification 22422 installed in production added 
interference fit plain bushings, in place of plain bushings. However, 
several occurrences of migration of the bushings were reported on those 
airplanes having Modification 22422 installed in production. 
Subsequently, Airbus has developed a further modification of the frame 
segment bushing, which entails removing the plain bushings and 
installing shouldered bushings on the frame used for attachment of the 
connection links. Airbus Modification 24497 accomplishes this 
installation for airplanes in production, using interference fit 
shouldered bushings. (For retrofit solutions, installation of the 
shouldered bushings is accomplished with Loctite sealant rather than 
interference fit).
    Airbus Service Bulletin A320-52-1027 is the retrofit solution 
equivalent to Modification 24497, to be accomplished on those airplanes 
in a pre-Modification 22422 configuration. For those airplanes on which 
Modification 22422 was installed in production, installation of 
shouldered bushings is also necessary, and is to be accomplished in 
accordance with the procedures described in Airbus Service Bulletin 
A320-52-1064. Accomplishment of the retrofit solution described in 
A320-52-1027 or A320-52-1064, as applicable, would terminate the 
repetitive inspection requirements of this AD. The FAA has revised the 
applicability and paragraphs (a), (b), (c), and (d) of the final rule 
to clarify the effectivity of the AD.

Request to Extend Compliance Time

    One commenter requests that the compliance time for accomplishing 
the initial detailed visual inspection be extended from the proposed 
450 flight hours to 460 flight hours, and that the repetitive interval 
be extended from the proposed 900 flight hours to 920 flight hours. The 
commenter states that such an extension will allow the inspection to be 
accomplished during a regularly scheduled ``A'' and ``2A'' check, and 
thereby eliminate any additional expenses that would be associated with 
special scheduling. The FAA does not concur. In developing an 
appropriate compliance time for this action, the

[[Page 38294]]

FAA considered the safety implications, parts availability, and normal 
maintenance schedules for timely accomplishment of the detailed visual 
inspection. Since maintenance schedules vary from operator to operator, 
there would be no assurance that the detailed visual inspection will be 
accomplished during a regularly scheduled ``A'' or ``2A'' check. 
However, under the provisions of paragraph (e) of the final rule, the 
FAA may approve requests for adjustments to the compliance time if data 
are submitted to substantiate that such an adjustment would provide an 
acceptable level of safety.

Correction to the Supplemental NPRM

    In paragraph (c) and in the Discussion section of the supplemental 
NPRM, the FAA made incorrect reference to the modification involving 
shouldered bushings, which would be required to be accomplished in 
accordance with Airbus Service Bulletin A320-57-1027, Revision 3, dated 
December 10, 1993. Although the supplemental NPRM specifies 
``replacement of the shouldered bushing on the locking mechanism with a 
new oversized bushing (Kit No. 521027A02)'', the modification entails 
installation of shouldered bushings on the frame segment used for 
attachment of the connection links, as the service bulletin specifies 
in reference to Kit No. 521027A02. Applicable portions of the preamble 
and paragraph (c) of this final rule have been revised to correctly 
describe the installation of shouldered bushings.

Conclusion

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

Cost Impact

    The FAA estimates that 94 Airbus Model A320 and Model A321 series 
airplanes of U.S. registry will be affected by this AD.
    It will take approximately 6 work hours per airplane to accomplish 
the required detailed visual inspection, at an average labor rate of 
$60 per work hour. Based on these figures, the cost impact of the 
detailed visual inspection required by this AD on U.S. operators is 
estimated to be $33,840, or $360 per airplane, per inspection cycle.
    For certain airplanes, it will take approximately 72 work hours per 
airplane to accomplish the required modification, at an average labor 
rate of $60 per work hour. Required parts will be supplied by the 
manufacturer at no cost to the operators. Based on these figures, the 
cost impact of the modification required by this AD on U.S. operators 
is estimated to be $4,320 per airplane.
    For certain other airplanes, it will take approximately 53 work 
hours per airplane to accomplish the required modification, at an 
average labor rate of $60 per work hour. Required parts will be 
supplied by the manufacturer at no cost to the operators. Based on 
these figures, the cost impact of the modification required by this AD 
on U.S. operators is estimated to be $3,180 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.

Regulatory Impact

    The regulations adopted herein will 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 final 
rule does not have sufficient federalism implications to warrant the 
preparation of a Federalism Assessment.
    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:

98-15-06  Airbus Industrie: Amendment 39-10657. Docket 94-NM-94-AD.

    Applicability: Model A320 and Model A321 series airplanes, as 
listed below, certificated in any category:
    <bullet> On which Airbus Modification 24497 has not been 
installed in production. Or
    <bullet> On which Airbus Service Bulletin A320-52-1027, Revision 
2, dated February 18, 1993, Revision 3, dated December 10, 1993, or 
Airbus Service Bulletin A320-52-1064, Revision 1, dated September 8, 
1995; has not been accomplished.

    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 has not been installed in production: 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 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

[[Page 38295]]

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 (c) 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, International Branch, ANM-116, FAA, Transport Airplane 
Directorate.
    (b) For Model A320 and Model A321 series airplanes on which 
Airbus Modification 22422 has been installed in production: 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, until the modification required by paragraph (d) of this AD 
is accomplished.
    (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 has not been installed in production: Within 3,500 flight 
hours after the effective date of this AD, install shouldered 
bushings on the frame segment used for attachment of the connection 
links (Kit No. 521027A02), in accordance with Airbus Service 
Bulletin A320-52-1027, Revision 3, dated December 10, 1993. 
Accomplishment of this modification constitutes terminating action 
for the repetitive inspection requirements of paragraph (a) of this 
AD.

    Note 2: Replacement in accordance with Airbus Service Bulletin 
A320-52-1027, Revision 2, dated February 18, 1993, is considered 
acceptable for compliance with the requirements of paragraph (c) of 
this AD.

    (d) For Model A320 and Model A321 series airplanes on which 
Airbus Modification 22422 has been installed in production: 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, 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 International Branch, ANM-116.

    (f) Special flight permits may be issued in accordance with 
Secs. 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.
    (g) Except for the repair action provided in paragraph 
(a)(2)(ii), the actions shall be done in accordance with the 
following Airbus Service Bulletins and All Operators Telex (AOT), 
which contain the specified list of effective pages:

--------------------------------------------------------------------------------------------------------------------------------------------------------
 Service bulletin and AOT referenced                                                      Rrevision level shown on                                      
              and date                                    Page No.                                  page                      Date shown on page        
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Service Bulletin A320-52-1047, April  1-15............................................  Original....................  April 25, 1994.                   
 25, 1994.                                                                                                                                              
AOT 52-07, July 28, 1994............  1-2.............................................  Original....................  July 28, 1994.                    
Service Bulletin A320-52-1066, March  1-13............................................  Original....................  March 6, 1995.                    
 6, 1995..                                                                                                                                              
Service Bulletin A320-52-1064,        1-4, 8, 21......................................  1...........................  September 8, 1995.                
 Revision 1, September 8, 1995..      5-7, 9-20.......................................  Original....................  November 28, 1994.                
Service Bulletin A320-53-1027,        1-6, 8, 11, 18, 19..............................  3...........................  December 10, 1993.                
 Revision 3, December 10, 1993.       37-42...........................................                                                                  
                                      7, 12, 14-17, 20-36.............................  1...........................  September 25, 1992                
                                      9, 10...........................................  Original....................  January 30, 1992.                 
                                      13..............................................  2...........................  February 18, 1993.                
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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 93-207-048(B), dated December 8, 1993.

    (h) This amendment becomes effective on August 20, 1998.

    Issued in Renton, Washington, on July 8, 1998.
S.R. Miller,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-18768 Filed 7-15-98; 8:45 am]
BILLING CODE 4910-13-U

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