[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