[Federal Register Volume 63, Number 225 (Monday, November 23, 1998)]
[Proposed Rules]
[Pages 64654-64655]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-31177]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-NM-284-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).
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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 a one-time
inspection of the forward engine mount assembly of the left and right
engines to verify that the part number on each assembly is correct; re-
identification of the forward engine mount assembly; and follow-on
actions, if necessary. This proposal is prompted by issuance of
mandatory continuing airworthiness information by a foreign civil
airworthiness authority. The actions specified by the proposed AD are
intended to prevent structural failure of the secondary load path of
the forward engine mount, which, if combined with failure of the
primary load path, could result in separation of the engine from the
airplane.
DATES: Comments must be received by December 23, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 98-M-284-D, 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: 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:
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 98-NM-284-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. 98-NM-284-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 modification of the forward
engine mount assembly of the left and right engines to meet increased
thrust load specifications, certain engine mount assemblies may not
have been modified properly. Improper modification of these assemblies
could cause the secondary load path of the forward engine mount to be
unable to sustain required loads, resulting in structural failure,
which, if combined with failure of the primary load path, could result
in separation of the engine from the airplane.
Explanation of Relevant Service Information
The manufacturer has issued Airbus Service Bulletin A320-71-1021,
Revision 01, dated June 10, 1998, which describes procedures for a one-
time visual inspection of the forward engine mount assembly of the left
and right engines to verify that the part number (P/N) on each assembly
is correct; re-identification of the forward engine mount assembly; and
follow-on actions, if necessary. If the P/N of the forward engine mount
is incorrect, the follow-on actions involve removal of the engine,
visual inspection to detect any crack or failure of the thrust links on
the forward engine mount assembly, modification of the engine mount if
no crack or failure is detected, or replacement of the existing thrust
link with a new thrust link and modification of the engine mount if any
crack or failure is detected.
Accomplishment of the actions specified in the Airbus service
bulletin is intended to adequately address the identified unsafe
condition. The Airbus service bulletin references V2500 International
Aero Engines Service Bulletin V2500-NAC-71-0135, Revision 1, dated
March 5, 1998, as an additional source of service information.
The DGAC classified the Airbus service bulletin as mandatory and
issued French airworthiness directive 98-293-118(B) dated July 29,
1998, 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.
[[Page 64655]]
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 Airbus service bulletin described
previously.
Cost Impact
The FAA estimates that 73 airplanes of U.S. registry would be
affected by this proposed AD, that it would take approximately 70 work
hours per airplane to accomplish the proposed inspection, and that the
average labor rate is $60 per work hour. Based on these figures, the
cost impact of the inspection proposed by this AD on U.S. operators is
estimated to be $306,600, or $4,200 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 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 98-NM-284-AD.
Applicability: Model A319-131 and -132, A320-232 and -233, and
A321-131 series airplanes; except those on which Airbus Modification
27020 has been accomplished (reference Airbus Service Bulletin A320-
71-1021, Revision 01, dated June 10, 1998); 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 (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 structural failure of the forward engine mount
secondary load path, which, if combined with failure of the primary
load path, could result in separation of the engine from the
airplane, accomplish the following:
(a) Within 500 flight hours after the effective date of this AD:
Perform a one-time visual inspection of the forward engine mount
assembly of the left and right engines to verify that the part
number (P/N) on each assembly is correct, in accordance with Airbus
Service Bulletin A320-71-1021, Revision 01, dated June 10, 1998.
(1) If the P/N on the forward engine mount assembly of the left
and right engines is 740-2010-513N or 740-2010-513 with a revision
of `N' or higher, prior to further flight, re-identify each assembly
in accordance with the service bulletin. No further action is
required by this AD.
(2) If the P/N on the forward engine mount assembly of the left
and right engines is different from the P/N's specified in paragraph
(a)(1) of this AD, or if the P/N cannot be determined: Prior to
further flight, perform a detailed visual inspection to detect any
crack or failure of the thrust links on each forward engine mount
assembly, in accordance with the service bulletin.
(i) If no crack or failure of any thrust link on the left or
right engine is detected: Within 2,250 landings following
accomplishment of the inspection specified in paragraph (a)(2) of
this AD, or at the next engine removal, whichever occurs first,
modify each engine mount and its installation, and re-identify each
forward engine mount assembly; in accordance with the service
bulletin.
(ii) If any crack or failure of any thrust link on the left or
right engine is detected, prior to further flight, replace the
existing thrust link with a new thrust link, modify each engine
mount, and re-identify each forward engine mount assembly; in
accordance with the service bulletin.
Note 2: Inspection and modification of the engine mount assembly
accomplished prior to the effective date of this AD in accordance
with Airbus Service Bulletin A320-71-1021, dated February 6, 1998,
is considered acceptable for compliance with the applicable actions
specified in this AD.
(b) As of the effective date of this AD, no person shall install
a forward engine mount assembly on any airplane equipped with
International Aero Engines (IAE) V2500-A5 engines, unless the
actions described in Airbus Service Bulletin A320-71-1021, dated
February 6, 1998, or Revision 01, dated June 10, 1998, have been
accomplished for that assembly.
Note 3: Airbus Service Bulletin A320-71-1021, Revision 01, dated
June 10, 1998, references V2500 IAE Service Bulletin V2500-NAC-71-
0135, Revision 1, dated March 5, 1998, as an additional source of
service information for accomplishment of the actions specified in
this AD.
(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, 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 4: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the International Branch, ANM-116.
(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 5: The subject of this AD is addressed in French
airworthiness directive 98-293-118(B), dated July 29, 1998.
Issued in Renton, Washington, on November 16, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-31177 Filed 11-20-98; 8:45 am]
BILLING CODE 4910-13-U
