[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:
On which Airbus Modification 24497 has not been
installed in production. Or
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:
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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
