[Federal Register Volume 60, Number 162 (Tuesday, August 22, 1995)]
[Rules and Regulations]
[Pages 43517-43519]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-19652]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 93-NM-121-AD; Amendment 39-9334; AD 95-17-05]
Airworthiness Directives; Airbus Model A310 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 all Airbus Model A310 series airplanes, that requires
inspections to detect loose self-locking nuts and damaged cotter pins
on the actuating cylinder to drag strut attachment of the left- and
right-hand main landing gear (MLG), and correction of discrepancies.
This amendment also provides an optional terminating action for the
repetitive inspections. This amendment is prompted by reports of loose
nuts and sheared cotter pins found on in-service airplanes. The actions
specified by this AD are intended to prevent an undampened free fall of
the left- and right-hand MLG, which subsequently could lead to the
inability to retract the MLG and damage to other airplane systems.
DATES: Effective September 21, 1995.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of September 21, 1995.
ADDRESSES: The service information referenced in this AD may be
obtained from Messier Services, 45635 Willow Pond Plaza, Sterling,
Virginia 20164. 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: Tim Backman, Aerospace Engineer,
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206)
227-2797; fax (206) 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 all Airbus Model A310 series
airplanes was published in the Federal Register on November 19, 1993
(58 FR 61037). That action proposed to require repetitive inspections
to detect loose self-locking nuts and damaged cotter pins on the
actuating cylinder to drag strut attachment of the left- and right-hand
main landing gear (MLG). That action also proposed to require
replacement of loose nuts with new washers and new nuts, and torque
tightening the nuts; replacement of damaged cotter pins with new cotter
pins; and submission of inspection reports.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the comments received.
One commenter supports the proposed rule.
Certain commenters request that the proposed rule be revised to
cite the latest revision of Messier Bugatti Airbus A310 Service
Bulletin 470-32-744 as an additional source of service information. The
FAA concurs. Since the issuance of the proposed rule, Messier Bugatti
(the manufacturer of the MLG assembly) has issued Revision 1 of Messier
Bugatti Airbus A310 Service Bulletin 470-32-744, dated January 13,
1994. This revised service bulletin is essentially identical to the
original version and does not entail any additional work. Therefore,
the final rule has been revised to reference Revision 1 of the service
bulletin as an additional source of service information.
Three commenters request that the FAA revise the proposal to
reference the accomplishment of the modification procedures described
in Messier Bugatti Airbus A310 Service Bulletin 470-32-760 as a
terminating modification for the repetitive inspection requirements.
One of these commenters states that the modification described in this
service bulletin includes a new hinge pin design that will preclude the
previously identified problems.
The FAA concurs. Since issuance of the proposed rule, Messier
Bugatti has issued Airbus A310 Service Bulletin 470-32-760, dated
December 31, 1993, as revised by Change Notice 1, dated January 28,
1994. This service bulletin describes procedures for modification of
the actuating cylinder/drag strut attachment of the MLG. The
modification entails modifying the greasing duct to enable simultaneous
rotation of the duct and cupel. The modification also entails modifying
the anti-warping washer to provide rotation play with the actuating
cylinder hinge pin. The modification will eliminate the risk of rupture
of the cotter pin. Accomplishment of this modification eliminates the
need for the repetitive inspections. Additionally, Airbus has issued
Service Bulletin A310-32-2076, Revision 1, dated December 13, 1994,
which references this Messier Bugatti service bulletin and is
essentially identical to it.
The Direction Generale de l'Aviation Civile (DGAC), which is the
airworthiness authority for France, classified these service bulletins
as mandatory. However, the FAA finds that the actions specified in the
service bulletins may be provided as an optional terminating
modification for the repetitive inspection requirements of the AD. The
FAA has determined not to mandate the modification, since the
inspection area is easily accessible, the discrepancies can be easily
detected, and the inspection is easily performed without the need to
remove any intervening structure. The FAA has added a new paragraph (c)
to the final rule, which provides for this
[[Page 43518]]
modification as optional terminating action for the required repetitive
inspections.
Additionally, since issuance of the notice, Airbus has issued
Service Bulletin A310-32-2069, Revision 1, dated December 13, 1994,
which references the Messier Bugatti Airbus A310 Service Bulletin 470-
32-744 that was cited in the proposal as the appropriate source of
service information for procedures to inspect the cotter pins. The
Airbus service bulletin is essentially identical to the corresponding
Messier Bugatti service bulletin. The DGAC classified these service
bulletins as mandatory in order assure the continued airworthiness of
these airplanes in France and issued French airworthiness directive 93-
039-143(B)R2, dated December 7, 1994, in order to assure the continued
airworthiness of these airplanes in France. The FAA has revised the
final rule to include these Airbus service bulletins as additional
sources of service information.
The FAA has reviewed the requirements of the proposed paragraphs
(a)(1) and (a)(2) and has determined that clarification is necessary.
The actions proposed in those paragraphs were intended to be parallel
to those recommended by the manufacturer in its referenced service
bulletin. The intent of these requirements was to require the
replacement of any loose nut and/or damaged cotter pin with a new nut,
washer, and cotter pin; and to require the installation of a new cotter
pin if no loose nut or no damaged cotter pin is found. However, as the
proposed AD was worded, operators could incorrectly interpret the
requirements as meaning that they must replace a loose nut only with a
new nut, and replace a damaged cotter pin only with a new cotter pin.
The operators also could incorrectly interpret the wording to mean that
the installation of a new cotter pin would not be necessary if a loose
nut or damaged cotter pin were found. In light of this, the FAA has
determined that the wording of proposed paragraphs (a)(1) and (a)(2)
must be revised to clarify its intent. These paragraphs of the final
rule contain the clarifying wording.
The FAA has recently reviewed the figures it has used over the past
several years in calculating the economic impact of AD activity. In
order to account for various inflationary costs in the airline
industry, the FAA has determined that it is necessary to increase the
labor rate used in these calculations from $55 per work hour to $60 per
work hour. The economic impact information, below, has been revised to
reflect this increase in the specified hourly labor rate.
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.
As a result of recent communications with the Air Transport
Association (ATA) of America, the FAA has learned that, in general,
some operators may misunderstand the legal effect of AD's on airplanes
that are identified in the applicability provision of the AD, but that
have been altered or repaired in the area addressed by the AD. The FAA
points out that all airplanes identified in the applicability provision
of an AD are legally subject to the AD. If an airplane has been altered
or repaired in the affected area in such a way as to affect compliance
with the AD, the owner or operator is required to obtain FAA approval
for an alternative method of compliance with the AD, in accordance with
the paragraph of each AD that provides for such approvals. A note has
been added to this final rule to clarify this long-standing
requirement.
The FAA estimates that 21 airplanes of U.S. registry will be
affected by this AD, that it will take approximately 1 work hour per
airplane to accomplish the required actions, and that the average labor
rate is $60 per work hour. Based on these figures, the total cost
impact of the AD on U.S. operators is estimated to be $1,260, or $60
per airplane, per inspection cycle.
The total 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.
Should an operator elect to accomplish the optional terminating
action that is provided by this AD action, the number of hours required
to accomplish it will be approximately 7 work hours per airplane, at an
average labor rate of $60 per work hour. Required parts will cost
approximately $1,968 per airplane. Based on these figures, the total
cost impact of the optional terminating action on U.S. operators would
be $2,388 per airplane.
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 USC 106(g), 40101, 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
95-17-05 Airbus Industrie: Amendment 39-9334. Docket 93-NM-121-AD.
Applicability: All Model A310 series airplanes, certificated in
any category.
Note 1: This AD applies to each airplane identified in the
preceding applicability provision, regardless of whether it has been
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 use the authority
provided in paragraph (d) of this AD to request approval from the
FAA. This approval may address either no action, if the current
configuration eliminates the unsafe condition; or different actions
necessary to address the unsafe condition described in this AD. Such
a request should include an assessment of the effect of the changed
configuration on the unsafe condition
[[Page 43519]]
addressed by this AD. In no case does the presence of any modification,
alteration, or repair remove any airplane from the applicability of
this AD.
Compliance: Required as indicated, unless accomplished
previously.
To prevent an undampened free fall of the left- and right-hand
main landing gear (MLG), which subsequently could lead to the
inability to retract the MLG and damage to other airplane systems,
accomplish the following:
(a) Within 60 days after the effective date of this AD, perform
an inspection to detect loose self-locking nuts and damaged (sheared
or marked) cotter pins on the actuating cylinder to drag strut
attachment of the left- and right-hand MLG, in accordance with
Messier Bugatti Airbus A310 Service Bulletin 470-32-744, dated March
31, 1993, or Revision 1, dated January 13, 1994; or Airbus Service
Bulletin A310-32-2069, Revision 1, dated December 13, 1994. Repeat
this inspection thereafter at intervals not to exceed 500 landings.
(1) If no nut is loose or no cotter pin is damaged, prior to
further flight, install a new cotter pin, in accordance with the
service bulletin. After replacement, continue to repeat the
inspection at intervals not to exceed 500 landings
(2) If any nut is loose or any cotter pin is damaged (sheared or
marked), prior to further flight, replace the nut, washer, and
cotter pin with a new nut, washer, and cotter pin; and torque
tighten the nut; in accordance with the service bulletin. After
replacement, continue to repeat the inspection at intervals not to
exceed 500 landings.
(b) Within 5 days after accomplishing the requirements of
paragraph (a) this AD, report all inspection results, positive or
negative, to Messier-Bugatti and Airbus Industrie in accordance with
Messier-Bugatti Airbus A310 Service Bulletin 470-32-744, dated March
31, 1993, or Revision 1, dated January 13, 1994. Information
collection requirements contained in this regulation have been
approved by the Office of Management and Budget (OMB) under the
provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et
seq.) and have been assigned OMB Control Number 2120-0056.
(c) Modification of the actuating cylinder/drag strut attachment
of the MLG, in accordance with Messier Bugatti Airbus A310 Service
Bulletin 470-32-760, dated December 31, 1993, as revised by Change
Notice 1, dated January 28, 1994; or Airbus Service Bulletin A310-
32-2076, Revision 1, dated December 13, 1994; constitutes
terminating action for the repetitive inspection requirements of
this AD.
(d) 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.
(e) 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.
(f) The inspection shall be done in accordance in accordance
with the following service bulletins, which contain the specified
list of effective pages:
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Revision level shown
Service bulletin referenced and date Page No. on page Date shown on page
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Messier Bugatti, 470-32-744, Mar. 31, 1993 1-7..................... Original............ Mar. 31, 1993.
Messier Bugatti, 470-32-744, Revision 1, 1-3, 5-6................ 1................... Jan. 13, 1994.
Jan. 13, 1994. 4....................... Original............ Mar. 31, 1993.
Airbus, A310-32-2069, Revision 1, Dec. 13, 1-6, 8-9, 13............ 1................... Dec. 13, 1994.
1994. 7, 10-12................ Original............ July 29, 1993.
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If accomplished, the modification shall be done in accordance with
Messier Bugatti Airbus A310 Service Bulletin 470-32-760, dated
December 31, 1993, as revised by Change Notice 1, dated January 28,
1994; or Airbus Service Bulletin A310-32-2076, Revision 1, dated
December 13, 1994, which contains the following list of effective
pages:
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Revision
Page No. level shown Date shown on page
on page
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1-2, 4-8........................... 1............ Dec. 13, 1994.
3, 9-11............................ Original..... Dec. 14, 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 Messier Services, 45635 Willow Pond
Plaza, Sterling, Virginia 20164. 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.
(g) This amendment becomes effective on September 21, 1995.
Issued in Renton, Washington, on August 3, 1995.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 95-19652 Filed 8-21-95; 8:45 am]
BILLING CODE 4910-13-U
