[Federal Register Volume 64, Number 78 (Friday, April 23, 1999)]
[Proposed Rules]
[Pages 19942-19945]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-10182]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-NM-62-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Industrie Model A300-600 Series
Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes the supersedure of 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 action would require repetitive ultrasonic
inspections to detect cracking in certain bolt holes of the rear spar,
and repair, if necessary. This proposal is prompted by issuance of
mandatory continuing airworthiness information by a foreign civil
airworthiness authority. The actions specified by the proposed 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: Comments must be received by May 24, 1999.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 98-NM-62-AD, 1601 Lind Avenue, SW., Renton,
Washington 98055-4056. Comments may be inspected at this location
between 9:00 a.m. and 3:00 p.m., Monday through Friday, except Federal
holidays.
The service information referenced in the proposed rule may be
obtained from Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707
Blagnac Cedex, France. This information may be examined at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington.
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:
Comments Invited
Interested persons are invited to participate in the making of the
proposed rule by submitting such written data, views, or arguments as
they may desire. Communications shall identify the Rules Docket number
and be submitted in triplicate to the address specified above. All
communications received on or before the closing date for comments,
specified above, will be considered before taking action on the
proposed rule. The proposals contained in this notice may be changed in
light of the comments received.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the proposed rule. All
comments submitted will be available, both before and after the closing
date for comments, in the Rules Docket for examination by interested
persons. A report summarizing each FAA-public contact concerned with
the substance of this
[[Page 19943]]
proposal will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this notice must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 98-NM-62-AD.'' The postcard will be date stamped and
returned to the commenter.
Availability of NPRMs
Any person may obtain a copy of this NPRM by submitting a request
to the FAA, Transport Airplane Directorate, ANM-114, Attention: Rules
Docket No. 98-NM-62-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
On September 20, 1995, the FAA issued AD 95-20-02, amendment 39-
9380 (60 FR 52618, October 10, 1995), applicable to certain Airbus
Industrie Model A300-600 series airplanes, to require repetitive high
frequency eddy current (HFEC) inspections to detect cracks in bolt
holes where parts of the main landing gear are attached to the rear
spar, and repair, if necessary. That action was prompted by a report
that cracks emanating from bolt holes in the rear spar were found
during full-scale fatigue testing. The requirements of that AD are
intended to prevent unnecessary degradation of the structural integrity
of the airframe due to cracks in the rear spar.
Explanation of Relevant Service Information
Since the issuance of AD 95-20-02, Airbus Industrie has issued
Service Bulletin A300-57-6017, Revision 2, dated January 14, 1997, and
Revision 3, dated November 19, 1997. Airbus Industrie Service Bulletin
A300-57-6017, Revision 2, describes procedures for an ultrasonic
inspection to be performed in lieu of the HFEC inspection that was
described in Revision 1, dated July 25, 1994. The ultrasonic inspection
method allows the inspection to be performed without removing bolts in
the area to be inspected, which is necessary for accomplishment of the
HFEC inspection described in Revision 1. Revision 3 of the service
bulletin adds new procedures for airplanes that have been inspected
previously in accordance with the original issue, dated November 22,
1993, or Revision 1 of the service bulletin. Accomplishment of the
actions specified in Airbus Industrie Service Bulletin A300-57-6017,
Revision 3, is intended to adequately address the identified unsafe
condition. The Direction Generale de l'Aviation Civile (DGAC), which is
the airworthiness authority for France, classified Revision 2 of this
service bulletin as mandatory and issued French airworthiness directive
94-031-155(B)R1, dated May 7, 1997, in order to assure the continued
airworthiness of these airplanes in France. The DGAC also approved
Revision 3 of this service bulletin.
Airbus Industrie also has issued Service Bulletin A300-57-6073,
dated September 30, 1997. That service bulletin describes procedures
for modification of certain bolt holes of the rear spar by oversizing
and cold working the bolt holes, and installing oversize studs. For
airplanes on which no cracks are found during the ultrasonic
inspections proposed by this AD, and on which Airbus Modification 07716
(reference Airbus Industrie Service Bulletin A300-57-6020, dated
November 22, 1993) has not been accomplished, accomplishment of the
modification described in service bulletin A300-57-6073 would eliminate
the need for the inspections described previously.
FAA's Conclusions
This airplane model is manufactured in France and is type
certificated for operation in the United States under the provisions of
Sec. 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the
applicable bilateral airworthiness agreement. Pursuant to this
bilateral airworthiness agreement, the DGAC has kept the FAA informed
of the situation described above. The FAA has examined the findings of
the DGAC, reviewed all available information, and determined that AD
action is necessary for products of this type design that are
certificated for operation in the United States.
Explanation of Requirements of Proposed Rule
Since an unsafe condition has been identified that is likely to
exist or develop on other airplanes of the same type design registered
in the United States, the proposed AD would supersede AD 95-20-02 to
require repetitive ultrasonic inspections to detect cracking in certain
bolt holes of the rear spar, and repair, if necessary. The actions
would be required to be accomplished in accordance with Revision 3 of
Airbus Industrie Service Bulletin A300-57-6017, described previously.
This proposed AD also would provide for optional terminating action for
the repetitive inspections.
Clarification of Repetitive Inspection Interval for Certain
Airplanes
The FAA finds that paragraph (c)(1) of the existing AD may be
misleading to operators in terms of specifying the applicable
repetitive inspection interval. Paragraph (c)(1) of the existing AD
states (for airplanes on which a crack was detected but on which Airbus
Industrie Modification 07716 has not been accomplished), ``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.'' The FAA finds that the repair procedures
specified in Airbus Industrie Service Bulletin 300-57-6017, Revision 1,
are substantially similar to those described in Airbus Industrie
Service Bulletin A300-57-6020, dated November 22, 1993 (which is the
service bulletin associated with Airbus Industrie Modification 07716).
Therefore, the FAA has determined that airplanes on which Airbus
Industrie Modification 07716 has not been accomplished, but on which
cracks were detected and repaired in accordance with Airbus Industrie
Service Bulletin 300-57-6017, Revision 1, should be subject to
repetitive inspections at the same interval as those airplanes on which
Airbus Industrie Modification 07716 has been accomplished. Note 4 has
been included in this proposal to clarify the intent of paragraph
(c)(1) of this AD.
Differences Between the Proposed Rule and the French Airworthiness
Directive
The proposed AD would differ from the parallel French airworthiness
directive in that the proposed AD would require accomplishment of the
repetitive ultrasonic inspections in accordance with Revision 3 of the
service bulletin. The French airworthiness directive specifies
accomplishment of the repetitive ultrasonic inspections in accordance
with Revision 2 of the service bulletin. The FAA's determination is
based on the fact that Revision 3 of the service bulletin includes
appropriate inspection thresholds and repetitive intervals for
airplanes inspected previously in accordance with Revision 1 of the
service bulletin. Because the existing AD requires accomplishment of
HFEC inspections in accordance with Revision 1 of the service bulletin,
the FAA finds that Revision 3 is the appropriate source of service
information for the inspections proposed by this AD.
[[Page 19944]]
Cost Impact
There are approximately 54 airplanes of U.S. registry that would be
affected by this proposed AD.
The new inspections that are proposed in this AD action would 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 proposed 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 figures discussed above are based on assumptions
that no operator has yet accomplished any of the proposed 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 proposed herein would 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 proposal would not have sufficient federalism
implications to warrant the preparation of a Federalism Assessment.
For the reasons discussed above, I certify that this proposed
regulation (1) is not a ``significant regulatory action'' under
Executive Order 12866; (2) is not a ``significant rule'' under the DOT
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979);
and (3) if promulgated, 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 copy of the draft
regulatory evaluation prepared for this action is contained in the
Rules Docket. A copy of it may be obtained by contacting the Rules
Docket at the location provided under the caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend
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 removing amendment 39-9380 (60 FR
52618, October 10, 1995), and by adding a new airworthiness directive
(AD), to read as follows:
Airbus Industrie: 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
[[Page 19945]]
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
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
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.
Note 7: The subject of this AD is addressed in French
airworthiness directive 94-031-155(B)R1, dated May 7, 1997.
Issued in Renton, Washington, on April 19, 1999.
D. L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 99-10182 Filed 4-22-99; 8:45 am]
BILLING CODE 4910-13-U
