[Federal Register Volume 64, Number 235 (Wednesday, December 8, 1999)]
[Rules and Regulations]
[Pages 68623-68625]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-31471]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-NM-284-AD; Amendment 39-11453; AD 99-25-10]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A319, A320, and 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 A319, A320, and A321 series
airplanes, that requires 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
amendment is prompted by issuance of mandatory continuing airworthiness
information by a foreign civil airworthiness authority. The actions
specified by this 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: Effective January 12, 2000.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of January 12, 2000.
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 A319, A320,
and A321 series airplanes was published in the Federal Register on
November 23, 1998 (63 FR 64654). That action proposed to 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.
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.
Two commenters state that they are not affected by the proposed
rule.
Request To Extend Compliance Time for Re-identification
One commenter, the manufacturer, requests that the FAA extend the
compliance time for the re-identification requirement in paragraph
(a)(1) of the proposed AD from ``prior to further flight'' to ``within
2,250 flight hours.'' The commenter states that such an extension would
allow operators more flexibility. The commenter points out that the
Direction Generale de l'Aviation Civile (DGAC), which is the
airworthiness authority for France, is planning to revise French
airworthiness directive 98-293-118(B), dated July 29, 1998 (which was
referenced in the NPRM as the appropriate corresponding French
airworthiness directive) on December 12, 1998, to allow this
flexibility of the compliance time.
The FAA partially concurs with the commenter's request. The FAA has
determined that there is no configuration difference, and therefore, it
is not necessary to accomplish the re-identification prior to further
flight. However, the FAA has determined that the required compliance
time should be specified in terms of landings, rather than flight
hours, to correspond to the compliance time specified in paragraph
(a)(2)(i) of the AD. The FAA has revised paragraph (a)(1) of this AD to
allow re-identification of the engine mounts within 2,250 landings
following accomplishment of the inspection specified in paragraph (a)
of this AD, or at the next engine removal, whichever occurs first. In
addition, the FAA has revised NOTE 7 (NOTE 5 of the proposed AD) of the
final rule to additionally reference French airworthiness directive 98-
293-118(B) R1, dated December 16, 1998.
Request To Withdraw the Re-identification Requirement
One commenter requests that the FAA not require re-identification
of the mounts, as required by paragraph (a)(2) of the proposed AD,
unless the configuration of the mount is altered. The commenter states
that the engine mount assembly re-identification serves no purpose
because there is no configuration difference between item number 740-
2020-513 ``N'' and -517. The commenter further states that all of the
mounts will be re-identified to a new part number when improved thrust
links are installed in accordance with Airbus Service Bulletin A320-71-
1020, dated May 25, 1998.
The FAA does not concur with the commenter's request.
Accomplishment of Service Bulletin A320-71-1020 is required by AD 99-
21-19, amendment 39-11364 (64 FR 55414, November 17, 1999). Because
there is other service information that affects the engine mount part
number, the FAA finds that the re-identification required by paragraph
(a)(2) of the AD is important to ensure proper control of the status of
the engine mounts.
Request for Relief From Removing Engines Simultaneously
One commenter requests relief from accomplishing the procedures in
paragraph B (4)(b) of Airbus Service Bulletin A320-71-1021, dated
February 6, 1998, or Revision 01, dated June 10, 1998, which states
that both engines must be modified at the same time. The commenter
notes that removal of both engines at the same time requires a flight
test, which increases the cost and time out-of-service.
The FAA concurs with the commenter's request. The FAA finds no
technical reason for the modification of both engines to occur at the
same time. However, both engines must be modified prior to 2,250
landings following accomplishment of the inspection or at the next
engine removal, whichever occurs first. The FAA has added a note after
paragraph (a)(2)(i) of the final rule to provide
[[Page 68624]]
clarification regarding accomplishment of the modification for each
engine.
Explanation of Change Made to Proposal
The FAA has clarified the inspection requirement contained in the
proposed AD. Whereas the proposal specified a visual inspection, the
FAA has revised this final rule to clarify that its intent is to
require a general visual inspection. Additionally, a note has been
added to the final rule to define that inspection.
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 described
previously. 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 73 airplanes of U.S. registry will be
affected by this AD, that it will take approximately 70 work hours per
airplane to accomplish the required inspection, and that the average
labor rate is $60 per work hour. Based on these figures, the cost
impact of the 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 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:
99-25-10 Airbus Industrie: Amendment 39-11453. 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:
Inspection and Follow-On Actions
(a) Within 500 flight hours after the effective date of this AD:
Perform a one-time general 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.
Note 2: For the purposes of this AD, a general visual inspection
is defined as ``A visual examination of an interior or exterior
area, installation, or assembly to detect obvious damage, failure,
or irregularity. This level of inspection is made under normally
available lighting conditions such as daylight, hangar lighting,
flashlight, or drop-light, and may require removal or opening of
access panels or doors. Stands, ladders, or platforms may be
required to gain proximity to the area being checked.''
(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: Within 2,250 landings following accomplishment of
the inspection specified in paragraph (a) of this AD, or at the next
engine removal, whichever occurs first, 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.
Note 3: Simultaneous modification of both engines is not
required.
(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 4: 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.
Note 5: Airbus Service Bulletin A320-71-1021, Revision 01, dated
June 10, 1998, references V2500 International Aero Engines (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.
Spares
(b) As of the effective date of this AD, no person shall install
a forward engine mount assembly on any airplane equipped with 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.
[[Page 68625]]
Alternative Methods of Compliance
(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 6: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the International Branch, ANM-116.
Special Flight Permits
(d) 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.
Incorporation by Reference
(e) The actions shall be done in accordance with Airbus Service
Bulletin A320-71-1021, Revision 01, dated June 10, 1998. 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 7: The subject of this AD is addressed in French
airworthiness directives 98-293-118(B), dated July 2, 1998, and 98-
293-118(B) R1, dated December 16, 1998.
(f) This amendment becomes effective on January 12, 2000.
Issued in Renton, Washington, on November 30, 1999.
D.L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 99-31471 Filed 12-7-99; 8:45 am]
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