[Federal Register Volume 60, Number 201 (Wednesday, October 18, 1995)]
[Rules and Regulations]
[Pages 53847-53849]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-25029]
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Rules and Regulations
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains regulatory documents
having general applicability and legal effect, most of which are keyed
to and codified in the Code of Federal Regulations, which is published
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The Code of Federal Regulations is sold by the Superintendent of Documents.
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Federal Register / Vol. 60, No. 201 / Wednesday, October 18, 1995 /
Rules and Regulations
[[Page 53847]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 94-NM-243-AD; Amendment 39-9395; AD 95-21-09]
Airworthiness Directives; Airbus Model A300 and A300-600 Series
Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment supersedes an existing airworthiness directive
(AD), applicable to all Airbus Model A300 series airplanes, that
currently requires repetitive inspections for cracking of the No. 2
flap beams, and replacement of the flap beams, if necessary. That AD
was prompted by reports of cracking of the No. 2 flap beams. This
amendment provides optional modifications for extending certain
inspection thresholds, and an optional terminating modification for
certain inspections. This amendment also expands the applicability of
the existing AD to include Model A300-600 series airplanes. The actions
specified by this AD are intended to prevent asymmetry of the flaps due
to cracking of the No. 2 flap beams.
DATES: Effective November 17, 1995.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of November 17, 1995.
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: 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) by superseding AD 85-07-04,
amendment 39-5027 (49 FR 45755, April 2, 1985), which is applicable to
all Airbus Model A300 series airplanes, was published in the Federal
Register on June 9, 1995 (60 FR 30471). That action proposed to
continue to require repetitive inspections for cracking of the No. 2
flap beams of Model A300 series airplanes, and replacement of the flap
beams, if necessary. That action also proposed to require identical
inspections of Model A300-600 series airplanes. Additionally, that
action proposed to provide an optional terminating modification for the
repetitive inspections on the Model 300-600 series airplanes, and
optional modifications for extending certain inspection thresholds for
Model A300 series airplanes.
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.
Another commenter also supports the proposed rule, but points out
that paragraph (d)(3) of the proposed AD contains a typographical
error. Paragraph (d)(3) should read ``perform the ultrasonic inspection
required by paragraph (d) of this AD.'' Paragraph (d)(3) currently
references paragraph (b). The FAA acknowledges a typographical error,
and has revised paragraph (d)(3) of the final rule accordingly.
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 change previously
described. The FAA has determined that this change will neither
increase the economic burden on any operator nor increase the scope of
the AD.
There are approximately 23 Model A300 series airplanes and 45 Model
A300-600 series airplanes of U.S. registry that will be affected by
this AD.
The inspections that are currently required by AD 85-07-04, and
applicable to the Model A300 series airplanes, take approximately 6
work hours per airplane, per inspection cycle, to accomplish at an
average labor rate of $60 per work hour. Based on these figures, the
total cost impact of the actions required by AD 85-07-04 on U.S.
operators of these airplanes is estimated to be $8,280, or $360 per
airplane, per inspection cycle.
The inspections that are required by this new AD, and applicable to
Model A300-600 series airplanes will take approximately 6 work hours
per airplane to accomplish, at an average labor rate of $60 per work
hour. Based on these figures, the total cost impact of these new
requirements on U.S. operators of these airplane is estimated to be
$16,200, or $360, per airplane, per inspection cycle.
The total 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.
Should an operator of a Model A300-600 series airplane elect to
accomplish the optional terminating action rather than continue the
repetitive inspections, it would take approximately 55 work hours to
accomplish it, at an average labor ate of $60 per work hour. Based on
these figures, the total cost impact of this optional terminating
action would be $3,300 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
[[Page 53848]]
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 removing amendment 39-5027 (49 FR
45755, April 2, 1985), and by adding a new airworthiness directive
(AD), amendment 39-9395, to read as follows:
95-21-09 Airbus Industrie: Amendment 39-9395. Docket 94-NM-243-AD.
Supersedes AD 85-07-04, Amendment 39-5027.
Applicability: All Model A300 and A300-600 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 (f) 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 asymmetry of the No. 2 flaps, accomplish the
following:
Note 2: Paragraph (a) of this AD restates the requirement for an
initial and repetitive inspections contained in paragraph A. of AD
85-07-04. Therefore, for operators who have previously accomplished
at least the initial inspection in accordance with AD 85-07-04,
paragraph (a) of this AD requires that the next scheduled inspection
be performed within the intervals specified in (a)(1), (a)(2), or
(a)(3), as applicable, after the last inspection performed in
accordance with paragraph A. of AD 85-07-04.
Note 3: Measurement of crack length is performed by measurement
of the probe displacement (perpendicular to symmetry plane of beam)
between defect indication appearance and its complete disappearance.
The bolt hole indication should not be interpreted as an indication
of a defect. These two indications appear very close together
because the defects originate from the bolt holes.
(a) For Model A300 series airplanes: Prior to the accumulation
of 15,000 total landings, or within the next 120 days after May 9,
1985 (the effective date of AD 85-07-04, amendment 39-5027),
whichever occurs later, inspect for cracking of the base steel
member and light alloy side members of the No. 2 flap beams, left
hand and right hand, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300-57-116, Revision 6,
dated July 16, 1993.
Note 4: Inspections required by paragraph (a) of this AD that
have been accomplished prior to the effective date of this AD in
accordance with Airbus Service Bulletin A300-57-116, Revision 1,
dated August 27, 1983; Revision 2, dated April 24, 1984; Revision 3,
dated July 20, 1984; Revision 4, dated August 13, 1986; or Revision
5, dated July 10, 1989; as applicable; are considered acceptable for
compliance with the applicable action specified in this amendment.
(1) If no cracking is detected: Except as provided by paragraph
(c) of this AD, repeat the inspection at intervals not to exceed
1,700 landings until the requirements of paragraph (b) of this AD
are accomplished.
(2) If any crack is detected that is less than or equal to 4 mm:
Repeat the inspection at intervals not to exceed 250 landings, until
the requirements of paragraph (b) of this AD are accomplished.
(3) If any crack is detected that exceeds 4 mm: Prior to further
flight, replace the flap beam in accordance with the service
bulletin, and prior to the accumulation of 15,000 flight cycles on
the replaced flap beam, perform the ultrasonic inspection as
required by paragraph (b) of this AD.
(b) For Model A300 series airplanes: Prior to the accumulation
of 15,000 total landings, or within the next 1,000 landings after
the effective date of this AD, whichever occurs later, perform an
ultrasonic inspection to detect cracking of the No. 2 flap beams, in
accordance with Airbus Service Bulletin No. A300-57-116, Revision 6,
dated July 16, 1993. Accomplishment of this inspection terminates
the inspection required by paragraph (a) of this AD.
(1) If no cracking is detected: Except as provided by paragraph
(c) of this AD, repeat the ultrasonic inspections thereafter at
intervals not to exceed 1,700 landings.
(2) If any crack is detected beyond the bolt hole, and that
crack is less than or equal to 4 mm in length: Repeat the ultrasonic
inspections thereafter at intervals not to exceed 250 landings.
(3) If any crack is detected beyond the bolt hole and that crack
is greater than 4 mm in length: Prior to further flight, replace the
flap beam in accordance with the service bulletin, and prior to the
accumulation of 15,000 flight cycles on the replaced flap beam,
perform the ultrasonic inspection as required by this paragraph.
(c) For Model A300 series airplanes: After accomplishing the
initial inspection required by paragraph (b) of this AD,
accomplishment of either paragraph (c)(1) or (c)(2) of this AD
extends the fatigue life of the No. 2 flap track beam as specified
in those paragraphs, provided that no cracking is detected during
any inspection required by paragraph (a) or (b) of this AD.
(1) Removal of any damage and the installation of larger
diameter bolts on the No. 2 flap track beam (Modification No. 4740),
in accordance with Airbus Service Bulletin No. A300-57-128, Revision
3, dated January 26, 1990, extends the interval for the first
repetitive inspection required by paragraph (b) of this AD from
1,700 landings to 12,000 landings, provided that Modification No.
4740 is accomplished prior to the accumulation of 16,700 total
landings on the flap beams. Following accomplishment of the first
repetitive inspection, subsequent repetitive inspections shall be
performed at intervals not to exceed 1,700 landings. Or
(2) Cold working of the bolt holes and the installation of
larger diameter bolts on the No. 2 flap track beam (Modification No.
5815), in accordance with Airbus Service Bulletin No. A300-57-141,
Revision 7, dated July 16, 1993, extends the interval for the first
repetitive inspection required by paragraph (b) of this AD from
1,700 landings to the interval specified in paragraph (c)(2)(i) or
(c)(2)(ii) of this AD.
(i) If interference fit bolts that are 15/32-inch in diameter
are fitted, the interval for the first repetitive inspection
required by paragraph (b) of this AD is extended to 22,000 landings,
provided that Modification 5815 is accomplished prior to the
accumulation of 16,700 total landings on the flap beam. Following
accomplishment of the first repetitive inspection required by
paragraph (b) of this AD, subsequent repetitive inspections shall be
performed at intervals not to exceed 1,700 landings. Or
(ii) If interference fit bolts that are 7/16- or 3/8-inch in
diameter are fitted, the interval for the first repetitive
inspection required by paragraph (b) of this AD is extended to
33,000 landings, provided that Modification 5815 is accomplished
prior to the accumulation of 16,700 total landings on the flap beam.
Following accomplishment of the first repetitive inspection required
by paragraph (b) of this AD, subsequent repetitive inspections shall
be performed at intervals not to exceed 1,700 landings.
(d) For Model A300-600 series airplanes: Prior to the
accumulation of 15,000 total
[[Page 53849]]
landings, or within the next 1,000 landings after the effective date of
this AD, whichever occurs later, perform an ultrasonic inspection to
detect cracking of the No. 2 flap track beams, in accordance with
Airbus Service Bulletin No. A300-57-6005, Revision 2, dated December
16, 1993.
(1) If no cracking is detected, repeat the ultrasonic
inspections thereafter at intervals not to exceed 1,700 landings.
(2) If any crack is detected beyond the bolt hole and that crack
is less than or equal to 4 mm in length: Repeat the ultrasonic
inspections thereafter at intervals not to exceed 250 landings.
(3) If any crack is detected beyond the bolt hole and that crack
is greater than 4 mm in length: Prior to further flight, replace the
flap beam in accordance with the service bulletin, and prior to the
accumulation of 15,000 landings on the replaced flap beam, perform
the ultrasonic inspection required by paragraph (d) of this AD.
(e) For Model A300-600 series airplanes: Installation of
oversized transition fit bolts in cold-worked holes, in accordance
with Airbus Service Bulletin No. A300-57-6006 (Modification 5815),
Revision 4, dated July 25, 1994, constitutes terminating action for
the repetitive inspection requirements of paragraph (d) of this AD,
provided that no cracking is detected during any inspection required
by paragraph (d) of this AD, and provided that the installation is
accomplished prior to the accumulation of 15,000 total landings. If
any bolt requires oversizing above 7/16-inch diameter during
accomplishment of this installation, prior to further flight, repair
in accordance with a method approved by the Manager, Standardization
Branch, ANM-113, FAA, Transport Airplane Directorate.
Note 5: If Airbus Service Bulletin No. A300-57-6005, Revision 2,
dated December 16, 1993, is accomplished concurrently with Airbus
Service Bulletin No. A300-57-6006 , Revision 3, dated December 16,
1993 (Modification 5815), the ultrasonic inspection for cracking
required by paragraph (d) of this AD need not be performed since the
eddy current inspection detailed for Modification 5815 is more
comprehensive.
(f) 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.
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 6: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Standardization Branch, ANM-113.
(g) 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.
(h) The actions shall be done in accordance with the following
Airbus service bulletins, which contain the specified list of
effective pages:
----------------------------------------------------------------------------------------------------------------
Revision level -
Service bulletin referenced and date- Page No. shown on page Date shown on page
----------------------------------------------------------------------------------------------------------------
A300-57-116, Revision 6, July 16, 1993.... 1-11 6 July 16, 1993.
A300-57-128, Revision 3, January 26, 1990. 1 3 January 26, 1990.
2-5 1 February 7, 1986.
6-14 Original August 27, 1983.
A300-57-141, Revision 7, July 16, 1993.... 1-24 7 July 16, 1993.
A300-57-6005, Revision 2, December 16, 1-4 2 December 16, 1993.
1993-.
5-7, 9 1 February 26, 1993.
8 Original August 13, 1986.
A300-57-6006, Revision 4, July 25, 1994... 1, 2, 5, 7 4 July 25, 1994.
3, 4, 6, 8-20 3 December 16, 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.
(i) This amendment becomes effective on November 17, 1995.
Issued in Renton, Washington, on October 3, 1995.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 95-25029 Filed 10-17-95; 8:45 am]
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