[Federal Register Volume 61, Number 18 (Friday, January 26, 1996)]
[Rules and Regulations]
[Pages 2410-2412]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-571]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 95-NM-66-AD; Amendment 39-9488; AD 96-02-03]
Airworthiness Directives; Airbus Model A310 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
[[Page 2411]]
ACTION: Final rule.
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SUMMARY: This amendment supersedes an existing airworthiness directive
(AD), applicable to all Airbus Model A310 series airplanes, that
currently requires inspections to detect cracks in the area of the
shock absorber attachment at the top of the barrel at the main landing
gear (MLG), a measurement of the gap between the barrel and the shock
absorber attachment; and corrective action, if necessary. That AD was
prompted by a report of the rupture of the aft hinge arm of the left
MLG barrel. This amendment requires a measurement of the gap between
the washer and barrel of the MLG, eddy current inspections to detect
cracking of the MLG barrel, correction of any discrepancy, and
accomplishment of certain other follow-on actions. Terminating actions
are also provided by this AD. The actions specified by this AD are
intended to prevent collapse of the MLG.
DATES: Effective February 26, 1996.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of February 26, 1996.
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: Phil Forde, Aerospace Engineer,
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, Washington 98055-4056; telephone (206)
227-2146; fax (206) 227-1149.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) by superseding AD 91-22-52,
amendment 39-8119 (57 FR 5372, February 14, 1992), which is applicable
to all Airbus Model A310 series airplanes, was published in the Federal
Register on November 8, 1995 (60 FR 56271). That action proposed to
require a measurement of the gap between the washer and barrel of the
main landing gear (MLG), eddy current inspections to detect cracking of
the MLG barrel, correction of any discrepancy, and accomplishment of
certain other follow-on actions.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the single comment received.
The commenter supports the proposed rule.
After careful review of the available data, including the comment
noted above, the FAA has determined that air safety and the public
interest require the adoption of the rule as proposed.
The FAA estimates that 18 airplanes of U.S. registry will be
affected by this proposed AD.
To accomplish the gap measurements, visual inspections, and other
follow-on actions will require approximately 5 work hours per airplane,
at an average labor rate of $60 per work hour. Based on these figures,
the cost impact of these required actions on U.S. operators is
estimated to be $5,400, or $300 per airplane, per cycle.
To accomplish the eddy current inspections will require
approximately 8 work hours per airplane, at an average labor rate of
$60 per work hour. Based on these figures, the cost impact of these
required inspections on U.S. operators is estimated to be $8,640, or
$480 per airplane, per inspection cycle.
Based on the figures discussed above, the cost impact of this AD on
U.S. operators is estimated to be $14,040, or $780 per airplane. The
cost impact figures 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.
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), 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by removing amendment 39-8119 (57 FR
5372, February 14, 1992), and by adding a new airworthiness directive
(AD), amendment 39-9488, to read as follows:
96-02-03 Airbus Industrie: Amendment 39-9488. Docket 95-NM-66-AD.
Supersedes AD 91-22-52, Amendment 39-8119.
Applicability: Model A310 series airplanes on which Airbus
Modification 1033 (reference Airbus Service Bulletin A310-32-2066,
Revision 1, dated January 30, 1992) has not been installed;
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 use the authority
provided in paragraph (e) 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 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 collapse of the main landing gear (MLG),
accomplish the following:
(a) Perform a measurement of the gap between the washer and
barrel at the times specified in paragraph (a)(1) or (a)(2) of this
AD, as applicable, in accordance with Messier Bugatti Airbus A310
Service Bulletin 470-32-726, Revision 2, dated February 8, 1994.
(1) For airplanes equipped with MLG barrels applicable to Table
No. 1 of the
[[Page 2412]]
service bulletin: Perform the measurement within 8 days after the
effective date of this AD.
(2) For airplanes equipped with MLG barrels applicable to Table
No. 2 of the service bulletin: Perform the measurement within 3
months after the effective date of this AD.
(b) If the gap measurement is less than 1 mm (0.04 in.):
Accomplish either paragraph (b)(1) or (b)(2) of this AD, as
applicable.
(1) For airplanes equipped with MLG barrels applicable to Table
No. 1 of the service bulletin: No further action is required by this
paragraph for those airplanes.
(2) For airplanes equipped with MLG barrels applicable to Table
No. 2 of the service bulletin: Prior to further flight, coat the MLG
barrel and shock absorber connecting rod nut with a rubber sealant
in accordance with Messier Bugatti Airbus A310 Service Bulletin 470-
32-726, Revision 2, dated February 8, 1994.
(c) If the gap is equal to or greater than 1 mm (0.04 in.):
Accomplish paragraphs (c)(1), (c)(2), and (c)(3) of this AD, as
applicable, in accordance with Messier Bugatti Airbus A310 Service
Bulletin 470-32-726, Revision 2, dated February 8, 1994.
(1) For all airplanes: Within 15 days after accomplishing the
measurement required by paragraph (a) of this AD, perform a gap
recovery procedure in accordance with paragraph 2.B.(5) of the
Accomplishment Instructions of the service bulletin.
(2) For airplanes equipped with MLG barrels applicable to Table
No. 2 of the service bulletin: Prior to further flight after
accomplishing the gap recovery procedure required by paragraph
(c)(1) of this AD, coat the MLG barrel and connecting rod nut with a
rubber sealant in accordance with the service bulletin.
(3) For all airplanes: Within 15 days after accomplishing the
measurement required by paragraph (a) of this AD, perform a visual
inspection to detect cracks of the MLG barrel, in accordance with
paragraph 2.B.1 of the Accomplishment Instructions of the service
bulletin.
(i) If no crack is detected: Repeat the visual inspection
thereafter at intervals not to exceed 7 days until the eddy current
inspection required by paragraph (d) of this AD is accomplished.
(ii) If any crack is detected: Prior to further flight, replace
the MLG barrel with a barrel that has been modified in accordance
with Messier Bugatti Service Bulletin 470-32-640, dated July 11,
1988, and Messier Bugatti Service Bulletin 470-32-763, dated
February 28, 1994. Accomplishment of this replacement shall be done
in accordance with Messier Bugatti Airbus A310 Service Bulletin 470-
32-726, Revision 2, dated February 8, 1994. After accomplishment of
this replacement, no further action is required by this AD.
(d) Except as provided by paragraph (c)(3)(ii) of this AD (MLG
barrel replacement): Following accomplishment of either paragraph
(b) or (c) of this AD, and at the applicable times specified in
Table No. 1 and Table No. 2 of Messier Bugatti Airbus A310 Service
Bulletin 470-32-726, Revision 2, dated February 8, 1994, remove the
rubber sealant and perform an eddy current inspection to detect
cracks of the MLG barrel in accordance with Table No. 3 of that
service bulletin.
(1) If no crack is detected: At the times specified in Table No.
3 of the service bulletin, perform the various follow-on actions in
accordance with the service bulletin. (The follow-on actions include
repetitive gap measurements, repetitive eddy current and visual
inspections, installation of a new bushing, and replacement of the
bronze washer with a stainless steel washer.)
(i) However, in lieu of installing a new bushing on crack-free
barrels having no oxidation of the cadmium plating at the next
overhaul, as specified in the service bulletin, operators must
either repeat the gap measurement and eddy current inspection at
intervals not to exceed 2 years, or install a new bushing and
replace the bronze washer at the upper part of the MLG barrel with a
stainless steel washer, in accordance with the service bulletin.
(ii) After accomplishment of the installation of a new bushing
(reference Messier Bugatti Service Bulletin 470-32-640) and the
replacement of the bronze washer (reference Messier Bugatti Service
Bulletin 470-32-763), no further action is required by this AD.
(2) If any crack is detected: Prior to further flight, replace
the barrel with a barrel that has been modified in accordance with
Messier Bugatti Service Bulletin 470-32-640, dated July 11, 1988,
and Messier Bugatti Service Bulletin 470-32-763, dated February 28,
1994. Accomplishment of this replacement shall be done in accordance
with the Messier Bugatti Airbus A310 Service Bulletin 470-32-726,
Revision 2, dated February 8, 1994. After accomplishment of this
replacement, no further action is required by 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, 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.
(f) 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.
(g) The actions shall be done in accordance with Messier Bugatti
Airbus A310 Service Bulletin 470-32-726, Revision 2, dated February
8, 1994. 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.
(h) This amendment becomes effective on February 26, 1996.
Issued in Renton, Washington, on January 11, 1996.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 96-571 Filed 1-25-96; 8:45 am]
BILLING CODE 4910-13-P
