[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