[Federal Register Volume 64, Number 144 (Wednesday, July 28, 1999)]
[Rules and Regulations]
[Pages 40743-40745]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-19155]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-NM-62-AD; Amendment 39-11236; AD 99-16-01]
RIN 2120-AA64
Airworthiness Directives; Airbus Industrie Model 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 certain Airbus Industrie Model A300-600 series
airplanes, that currently requires repetitive high frequency eddy
current inspections to detect cracks in bolt holes where parts of the
main landing gear are attached to the rear spar, and repair, if
necessary. This amendment requires repetitive ultrasonic inspections to
detect cracking in certain bolt holes of the rear spar, and repair, 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 detect and
correct cracking of the rear spar of the wing, which could result in
reduced structural integrity of the airplane.
DATES: Effective September 1, 1999.
The incorporation by reference of Airbus Industrie Service Bulletin
A300-57-6017, Revision 3, dated November 19, 1997, as listed in the
regulations is approved by the Director of the Federal Register as of
September 1, 1999.
The incorporation by reference of Airbus Industrie Service Bulletin
A300-57-6017, Revision 1 (includes Appendix 1), dated July 25, 1994, as
listed in the regulations was approved previously by the Director of
the Federal Register as of November 9, 1995 (60 FR 52618, October 10,
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: 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) by superseding AD 95-20-02,
amendment 39-9380 (60 FR 52618, October 10, 1995), which is applicable
to certain Airbus Industrie Model A300-600 series airplanes, was
published in the Federal Register on April 23, 1999 (64 FR 19942). The
action proposed to require repetitive ultrasonic inspections to detect
cracking in certain bolt holes of the rear spar, and repair, if
necessary.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. No comments were submitted in response
to the proposal or the FAA's determination of the cost to the public.
Conclusion
The FAA has determined that air safety and the public interest
require the adoption of the rule as proposed.
Cost Impact
There are approximately 54 airplanes of U.S. registry that will be
affected by this AD.
The new inspections that are required by this AD will take
approximately 226 work hours per airplane to accomplish, at an average
labor rate of $60 per work hour. Based on these figures, the cost
impact of the new requirements of this AD on U.S. operators is
estimated to be $732,240, or $13,560 per airplane, per inspection
cycle.
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:
[[Page 40744]]
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 removing amendment 39-9380 (60 FR
52618, October 10, 1995), and by adding a new airworthiness directive
(AD), amendment 39-11236, to read as follows:
99-16-01 Airbus Industrie: Amendment 39-11236. Docket 98-NM-62-AD.
Supersedes AD 95-20-02, Amendment 39-9380.
Applicability: Model A300-600 series airplanes, having
manufacturer's serial numbers (MSN) 252 through 553 inclusive,
certificated in any category; except those airplanes on which Airbus
Industrie Production Modification No. 07601 has been accomplished
prior to delivery.
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 (h) 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 detect and correct cracking of the rear spar of the wing,
which could result in reduced structural integrity of the airplane,
accomplish the following:
Restatement of Requirements of AD 95-20-02:
Note 2: Accomplishment of the inspections and repair of cracking
in accordance with Airbus Industrie Service Bulletin A300-57-6017,
dated November 22, 1993, prior to November 9, 1995 (the effective
date of AD 95-20-02, amendment 39-9380), is acceptable for
compliance with the applicable action specified in this amendment.
(a) Perform a high frequency eddy current (HFEC) rototest
inspection to detect cracks in certain bolt holes where the main
landing gear (MLG) forward pick-up fitting and MLG rib 5 aft are
attached to the rear spar, in accordance with Airbus Industrie
Service Bulletin A300-57-6017, Revision 1 (includes Appendix 1),
dated July 25, 1994.
Note 3: This service bulletin also references Airbus Industrie
Service Bulletin A300-57-6020, dated November 22, 1993, as an
additional source of service information.
(1) For airplanes that have accumulated 17,300 total landings or
less as of November 9, 1995: Inspect prior to the accumulation of
17,300 total landings, or within 1,500 landings after November 9,
1995, whichever occurs later.
(2) For airplanes that have accumulated 17,301 or more total
landings, but less than 19,300 total landings as of November 9,
1995: Inspect within 1,500 landings after November 9, 1995.
(3) For airplanes that have accumulated 19,300 or more total
landings as of November 9, 1995: Inspect within 750 landings after
November 9, 1995.
(b) If no crack is found during the inspection required by
paragraph (a) of this AD, repeat that inspection thereafter at the
time specified in either paragraph (b)(1) or (b)(2) of this AD, as
applicable.
(1) For airplanes on which Airbus Industrie Modification 07716
(as described in Airbus Industrie Service Bulletin A300-57-6020) has
not been accomplished, inspect at the time specified in paragraph
(b)(1)(i) or (b)(1)(ii) of this AD, as applicable.
(i) For airplanes having MSN 465 through 553 inclusive: Repeat
the inspection at intervals not to exceed 13,000 landings, until the
inspection required by paragraph (d)(2)(i)(A) has been accomplished.
(ii) For airplanes having MSN 252 through 464 inclusive: Repeat
the inspection at intervals not to exceed 8,400 landings, until the
inspection required by paragraph (d)(2)(i)(B) has been accomplished.
(2) For airplanes on which Airbus Industrie Modification 07716
has been accomplished, inspect at the time specified in either
paragraph (b)(2)(i) or (b)(2)(ii) of this AD, as applicable.
(i) For airplanes having MSN 465 through 553 inclusive: Repeat
the inspection at intervals not to exceed 11,800 landings, until the
inspection required by paragraph (d)(2)(ii)(A) has been
accomplished.
(ii) For airplanes having MSN 252 through 464 inclusive: Repeat
the inspection within 10,700 landings following the initial
inspection required by paragraph (a) of this AD, and thereafter at
intervals not to exceed 7,500 landings, until the inspection
required by paragraph (d)(2)(ii)(B) has been accomplished.
(c) If any crack is found during the inspection required by
either paragraph (a) or (b) of this AD, prior to further flight,
accomplish the requirements of either paragraph (c)(1) or (c)(2) of
this AD, as applicable.
(1) For airplanes on which Airbus Industrie Modification 07716
has not been accomplished: Oversize the bolt hole by 1/32 inch and
repeat the HFEC inspection required by paragraph (a) of this AD, in
accordance with Airbus Industrie Service Bulletin 300-57-6017,
Revision 1, dated July 25, 1994. After accomplishing the oversizing
and HFEC inspection, repeat the inspection as required by paragraph
(b) of this AD at the applicable schedule specified in that
paragraph, until the inspection required by paragraph (d)(2)(ii)(A)
has been accomplished.
Note 4: For the purposes of this AD, airplanes that are repaired
in accordance with Airbus Industrie Service Bulletin 300-57-6017,
Revision 1, are considered to be subject to repetitive inspections
at the same interval as those airplanes on which Airbus Industrie
Modification 07716 has been accomplished.
(i) If no cracking is detected, install the second oversize bolt
in accordance with the service bulletin.
(ii) If any cracking is detected, repair in accordance with a
method approved by the Manager, International Branch, ANM-116, FAA,
Transport Airplane Directorate.
(2) For airplanes on which Airbus Industrie Modification 07716
has been accomplished: Repair in accordance with a method approved
by the Manager, International Branch, ANM-116. After repair, repeat
the inspections as required by paragraph (b) of this AD at the
applicable schedule specified in that paragraph, until the
inspection required by paragraph (d)(2)(ii)(B) has been
accomplished.
New Requirements of This AD
New Initial and Repetitive Inspections
(d) Perform an ultrasonic inspection to detect cracks in certain
bolt holes where the MLG forward pick-up fitting and MLG rib 5 aft
are attached to the rear spar, in accordance with Airbus Industrie
Service Bulletin A300-57-6017, Revision 3, dated November 19, 1997;
at the time specified in paragraph (d)(1) or (d)(2) of this AD, as
applicable.
Note 5: Inspections accomplished prior to the effective date of
this AD in accordance with Airbus Industrie Service Bulletin A300-
57-6017, Revision 2, dated January 14, 1997, are considered
acceptable for compliance with paragraph (d) of this AD.
(1) For airplanes not inspected prior to the effective date of
this AD in accordance with Airbus Industrie Service Bulletin A300-
57-6017, dated November 22, 1993, or Revision 1 (includes Appendix
1), dated July 25, 1994: Inspect at the time specified in paragraph
(d)(1)(i), (d)(1)(ii), or (d)(1)(iii) of this AD, as applicable.
Accomplishment of this inspection terminates the requirements of
paragraph (a) of this AD.
(i) For airplanes that have accumulated 17,300 total landings or
fewer as of the effective date of this AD: Inspect prior to the
accumulation of 17,300 total landings, or within 1,500 landings
after the effective date of this AD, whichever occurs later.
(ii) For airplanes that have accumulated 17,301 total landings
or more but fewer than 19,300 total landings as of the effective
date of this AD: Inspect within 1,500 landings after the effective
date of this AD.
(iii) For airplanes that have accumulated 19,300 total landings
or more as of the effective date of this AD: Inspect within 750
landings after the effective date of this AD.
(2) For airplanes on which an HFEC inspection was performed
prior to the effective date of this AD in accordance with paragraph
(a) of AD 95-20-02, or in accordance with Airbus Industrie Service
Bulletin A300-57-6017, dated November 22, 1993: Inspect at the time
specified in paragraph (d)(2)(i) or (d)(2)(ii), as applicable.
(i) If no cracking was detected during any HFEC inspection
accomplished prior to the effective date of this AD, and if Airbus
[[Page 40745]]
Industrie Modification 07716 has not been accomplished: Inspect at
the time specified in paragraph (d)(2)(i)(A) or (d)(2)(i)(B) of this
AD, as applicable.
(A) For airplanes having MSN 465 through 553 inclusive: Inspect
within 13,000 landings after the most recent HFEC inspection, and
thereafter at intervals not to exceed 8,900 landings. Accomplishment
of this inspection constitutes terminating action for the repetitive
inspection requirement of paragraph (b)(1)(i) of this AD.
(B) For airplanes having MSN 252 through 464 inclusive: Inspect
within 8,400 landings after the most recent HFEC inspection, and
thereafter at intervals not to exceed 5,500 landings. Accomplishment
of this inspection constitutes terminating action for the repetitive
inspection requirement of paragraph (b)(1)(ii) of this AD.
(ii) If any cracking was detected during any HFEC inspection
performed prior to the effective date of this AD, regardless of the
method of repair, or if Airbus Industrie Modification 07716 has been
accomplished: Inspect at the time specified in paragraph
(d)(2)(ii)(A) or (d)(2)(ii)(B) of this AD, as applicable.
(A) For airplanes having MSN 465 through 553 inclusive: Inspect
within 11,800 landings after the most recent HFEC inspection, and
thereafter at intervals not to exceed 8,200 landings. Accomplishment
of this inspection constitutes terminating action for the repetitive
inspection requirement of paragraph (c)(1) or (c)(2) of this AD, as
applicable.
(B) For airplanes having MSN 252 through 464 inclusive: Inspect
within 10,700 landings after the initial inspection in accordance
with paragraph (a) of AD 95-20-02, or within 7,500 landings after
the most recent HFEC inspection, whichever occurs later, and
thereafter at intervals not to exceed 4,900 landings. Accomplishment
of this inspection constitutes terminating action for the repetitive
inspection requirement of paragraph (c)(1) or (c)(2) of this AD, as
applicable.
(e) If no cracking is detected during the ultrasonic inspection
required by paragraph (d)(1) of this AD, repeat that inspection
thereafter at the time specified in paragraph (e)(1) or (e)(2) of
this AD, as applicable.
(1) For airplanes having MSN 465 through 553 inclusive: Repeat
the inspection at intervals not to exceed 8,900 landings.
(2) For airplanes having MSN 232 through 464 inclusive: Repeat
the inspection at intervals not to exceed 5,500 landings.
Repair
(f) If any cracking is detected during any inspection performed
in accordance with paragraph (d) or (e) of this AD: Prior to further
flight, repair in accordance with a method approved by the Manager,
International Branch, ANM-116; or the Direction Generale de
l'Aviation Civile (or its delegated agent).
Terminating Action
(g) Accomplishment of Airbus Industrie Modification 11440
(Airbus Industrie Service Bulletin A300-57-6073, dated September 30,
1997) constitutes terminating action for the repetitive inspection
requirements of paragraphs (d) and (e) of this AD, as applicable.
Alternative Methods of Compliance
(h) 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.
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
(i) 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
(j) Except as provided by paragraphs (c)(1)(ii), (c)(2), (f),
and (g) of this AD, the actions shall be done in accordance with
Airbus Industrie Service Bulletin A300-57-6017, Revision 1 (includes
Appendix 1), dated July 25, 1994, and Airbus Industrie Service
Bulletin A300-57-6017, Revision 3, dated November 19, 1997. The
incorporation by reference of Airbus Industrie Service Bulletin
A300-57-6017, Revision 3, dated November 19, 1997 is approved by the
Director of the Federal Register in accordance with 5 U.S.C. 552(a)
and 1 CFR part 51. The incorporation by reference of Airbus
Industrie Service Bulletin A300-57-6017, Revision 1 (includes
Appendix 1), dated July 25, 1994, was approved previously by the
Director of the Federal Register as of November 9, 1995 (60 FR
52618, October 10, 1995). 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 directive 94-031-155(B)R1, dated May 7, 1997.
(k) This amendment becomes effective on September 1, 1999.
Issued in Renton, Washington, on July 21, 1999.
D. L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 99-19155 Filed 7-27-99; 8:45 am]
BILLING CODE 4910-13-P
