[Federal Register Volume 61, Number 21 (Wednesday, January 31, 1996)]
[Proposed Rules]
[Pages 3343-3346]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-1874]



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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 94-NM-102-AD]


Airworthiness Directives; Airbus Model A300 B2 and B4 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 all Airbus Model A300 B2, 
B4-100, and B4-200 series airplanes, that currently requires 
supplemental structural inspections to detect fatigue cracking, and 
repair of cracked structure. This action would require revising the 
supplemental structural inspection program, including changing some of 
the inspection techniques, changing some of the thresholds and 
intervals for inspections, expanding the area to be inspected for some 
of the inspections, and revising the Fleet Leader Program. This 
proposal is prompted by a review of in-service history and reports 
received from the current supplemental structural inspections program 
required by the existing AD. The actions specified by the proposed AD 
are intended to prevent reduced structural integrity of these airplanes 
due to fatigue cracking.

DATES: Comments must be received by March 11, 1996.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-103, 
Attention: Rules Docket No. 94-NM-102-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9 a.m. and 3 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:
Phil Forde, Aerospace Engineer, Standardization Branch, ANM-113, FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington 98055-4056; telephone (206) 227-2146; fax (206) 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 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 94-NM-102-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-103, Attention: Rules 
Docket No. 94-NM-102-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

[[Page 3344]]


Discussion

    On January 15, 1993, the FAA issued AD 93-01-24, amendment 39-8478 
(58 FR 6703, February 2, 1993), applicable to all Airbus Model A300 B2, 
B4-100, and B4-200 series airplanes. That AD requires supplemental 
structural inspections to detect fatigue cracking, and repair or 
replacement of cracked structure, if necessary. That action was 
prompted by a structural re-evaluation, which identified certain 
significant structural components that are to be inspected to detect 
fatigue cracking as these airplanes approach or exceed the design 
service goal. The requirements of that AD are intended to prevent 
reduced structural integrity of these airplanes.
    Since the issuance of that AD, Airbus has issued ``Airbus Industrie 
A300 Supplemental Structural Inspection Document'' (SSID), Revision 2, 
dated June 1994. This revision of the SSID includes the following 
changes:
    a. changes to some of the inspection techniques,
    b. changes to some of the thresholds and intervals for certain 
inspections,
    c. expands the area to be inspected for some of the inspections, 
and
    d. revises the Fleet Leader Program.
    The Direction Generale de l'Aviation Civile (DGAC), which is the 
airworthiness authority for France, classified this document as 
mandatory and issued French airworthiness directive 89-109-097(B)R7, 
dated June 7, 1995, in order to assure the continued airworthiness of 
these airplanes in France.
    This airplane model is manufactured in France and is type 
certificated for operation in the United States under the provisions of 
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and 
the applicable bilateral airworthiness agreement. Pursuant to this 
bilateral airworthiness agreement, the French DGAC has kept the FAA 
informed of the situation described above. The FAA has examined the 
findings of the French 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.
    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 93-01-24 to 
continue to require supplemental structural inspections to detect 
fatigue cracking, and repair of cracked structure. This proposed AD 
would require revising the supplemental structural inspection program, 
including changing some of the inspection techniques, changing some of 
the thresholds and intervals for certain inspections, expanding the 
area to be inspected for some of the inspections, and revising the 
Fleet Leader Program. The actions would be required to be accomplished 
in accordance with the SSID described previously.
    Although paragraph 6.2, ``Complete RR Method,'' of Section 9 of the 
SSID provides operators the option of calculating inspection thresholds 
and intervals using the ``risk ratio (RR),'' operators should note that 
the proposed AD does not permit operators the option of using the RR in 
their calculations. This is in consonance with actions taken by the 
DGAC; it is no longer approving maintenance inspection programs that 
have used the RR to calculate the inspection thresholds and intervals.
    The FAA estimates that approximately 26 Model A300 series airplanes 
of U.S. registry would be affected by this proposed AD.
    The actions that are currently required by AD 93-01-24 take 
approximately 564 work hours per airplane to accomplish, at an average 
labor rate of $60 per work hour. Based on these figures, the cost 
impact on U.S. operators of the actions currently required is estimated 
to be $879,840, or $33,840 per airplane.
    Implementation of the inspections, repairs, or replacements 
specified in Revision 2 of the SSID into an operator's maintenance 
program is estimated to require approximately 597 work hours (including 
removal, inspection, and installation work hours) per airplane per 
year, at an average labor rate of $60 per work hour. Based on these 
figures, the cost impact on U.S. operators of the proposed requirements 
of this AD is estimated to be $931,320, or $35,820 per airplane.
    The cost impact figures discussed above are based on assumptions 
that no operator has yet accomplished any of the current or proposed 
requirements of this AD action, and that no operator would accomplish 
those actions in the future if this AD were not adopted.
    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 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 USC 106(g), 40113, 44701.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by removing amendment 39-8478 (58 FR 
6703, February 2, 1993), and by adding a new airworthiness directive 
(AD), to read as follows:

Airbus Industrie: Docket 94-NM-102-AD. Supersedes AD 93-01-24, 
Amendment 39-8478.

    Applicability: All Model A300 B2-1A, B2-1C, B2K-3C, and B2-203 
series airplanes, and A300 B4-2C, B4-103, and B4-203 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 (m) 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 

[[Page 3345]]
repair remove any airplane from the applicability of this AD.

    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent reduced structural integrity of these airplanes due 
to fatigue cracking, accomplish the following:
    (a) Within one year after March 9, 1993 (the effective date of 
AD 93-01-24, amendment 39-8478), incorporate a revision into the 
FAA-approved maintenance inspection program that provides for 
supplemental maintenance inspections, modifications, repair, or 
replacement of the significant structural details (SSD) and 
significant structural items (SSI) specified in ``Airbus Industrie 
A300 Supplemental Structural Inspection Document'' (SSID), dated 
September 1989 (hereafter referred to as ``the SSID'').
    (b) Within one year after the effective date of this AD, replace 
the revision of the FAA-approved maintenance program required by 
paragraph (a) of this AD with the inspections, inspection intervals, 
repairs, and replacements defined in ``Airbus Industrie A300 
Supplemental Structural Inspection Document'' (SSID), Revision 2, 
dated June 1994 (hereafter referred to as ``Revision 2 of the 
SSID''). Accomplish the actions specified in the service bulletins 
identified in Section 6, ``SB Reference List,'' Revision 2 of the 
SSID, at the times specified in those service bulletins. The actions 
are to be accomplished in accordance with those service bulletins.
    (1) For airplanes that have exceeded the threshold specified in 
any of the service bulletins identified in Section 6, ``SB Reference 
List,'' Revision 2 of the SSID: Accomplish the actions specified in 
those service bulletins within the grace period specified in that 
service bulletin. The grace period is to be measured from the 
effective date of this AD.
    (2) For airplanes that have exceeded the threshold specified in 
any of the service bulletins identified in Section 6, ``SB Reference 
List,'' Revision 2 of the SSID, and a grace period is not specified 
in that service bulletin: Accomplish the actions specified in that 
service bulletins within 1,500 flight cycles after the effective 
date of this AD.
    (c) If any cracked structure is detected during the inspections 
required by either paragraph (a) or (b) of this AD, prior to further 
flight, permanently repair the cracked structure in accordance with 
either paragraph (c)(1), (c)(2), or (c)(3) of this AD.

    Note: A permanent repair is defined as a repair that meets the 
certification basis of the airplane, and does not require additional 
modification at a later date.

    (1) The service bulletins listed in Section 6, ``SB Reference 
List,'' of the SSID [for airplanes that are currently being 
inspected in accordance with paragraph (a) of this AD]; or in 
accordance with a method approved by the Manager, Standardization 
Branch, ANM-113, FAA, Transport Airplane Directorate, if a permanent 
repair is not specified in any of these service bulletins. Or
    (2) The service bulletins listed in Section 6, ``SB Reference 
List,'' of Revision 2 of the SSID [for airplanes that are currently 
being inspected in accordance with paragraph (b) of this AD]; or in 
accordance with a method approved by the Manager, Standardization 
Branch, ANM-113, if a permanent repair is not specified in any of 
these service bulletins. Or
    (3) Other permanent repair data meeting the certification basis 
of the airplane which is approved by the Manager, Standardization 
Branch, ANM-113, or by the Direction Generale de l'Aviation Civil 
(DGAC) of France.
    (d) For airplanes identified as Fleet Leader Program (FLP) in 
Section 5, ``Fleet Leader Program,'' of the SSID or Revision 2 of 
the SSID: Inspect according to the instructions and intervals 
specified in paragraph 4.4, ``Adjustment of Inspection Requirements 
and DSG,'' of Section 4, or Section 9, as applicable, of the SSID 
[for airplanes inspected in accordance with paragraph (a) of this 
AD], or Revision 2 of the SSID [for airplanes inspected in 
accordance with paragraph (b) of this AD], for each SSD.
    (e) For the purpose of accomplishing paragraphs (d), (f), (g), 
and (i) of this AD, operators shall not use paragraph 6.2, 
``Complete RR Method,'' of Section 9 of the SSID to calculate 
inspection thresholds and intervals.
    (f) For Model A300-B2 and B2K-3C series airplanes: For any SSD 
that has exceeded the values of the threshold specified in paragraph 
6, ``Inspection Threshold and Intervals,'' Section 9 of the SSID, 
inspect at the time specified in either paragraph (f)(1) or (f)(2) 
of this AD, as applicable.
    (1) For airplanes inspected in accordance with paragraph (a) of 
this AD: Inspect within 2,000 landings after March 9, 1993, in 
accordance with the SSID. Or
    (2) For airplanes inspected in accordance with paragraph (b) of 
this AD: Inspect within 2,000 landings after the effective date of 
this AD, in accordance with Revision 2 of the SSID.
    (g) For Model A300-B4 series airplanes: For any SSD that has 
exceeded the values of the threshold specified in paragraph 6, 
``Inspection Threshold and Intervals,'' Section 9 of the SSID, 
inspect at the time specified in either paragraph (g)(1) or (g)(2) 
of this AD, as applicable.
    (1) For airplanes inspected in accordance with paragraph (a) of 
this AD: Inspect within 1,500 landings after March 9, 1993 [the 
effective date of AD 93-01-24, amendment 39-8478]. Or
    (2) For airplanes inspected in accordance with paragraph (b) of 
this AD: Inspect within 1,500 landings after the effective date of 
this AD.
    (h) For airplanes identified as FLP in Section 5, ``Fleet Leader 
Program,'' of the SSID or Revision 2 of the SSID: Within one year 
after the effective date of this AD, apply the basic requirements 
given in Revision 2 of the SSID.
    (i) For airplanes that are subject to the requirements of 
paragraph (b) of this AD, and have exceeded the initial inspection 
threshold specified in paragraph 4.4, ``Adjustment of Inspection 
Requirements and DSG,'' of Section 4, or paragraph 6, ``Inspection 
Threshold and Intervals,'' of Section 9, for each SSD: Perform the 
initial inspection prior to the accumulation of the number of flight 
cycles specified in paragraph 7, ``Additional Information,'' Section 
9, of Revision 2 of the SSID.

    Note 3: Fatigue ratings are not applicable to these allowances; 
therefore, no adjustment is required.

    Note 4: Paragraph (i) of this AD provides the ``grace'' periods 
for those airplanes that are new to the FLP or that have newly added 
or revised SSID requirements in accordance with paragraph (b) of 
this AD.

    (j) The grace period provided by paragraph (i) of this AD is 
also applicable to the thresholds and/or repeat intervals for each 
SSD for which the inspection interval or threshold was reduced in 
accordance with the requirements of paragraph (b) of this AD.
    (k) For FLP airplanes identified in Section 5, ``Fleet Leader 
Program,'' of the SSID or Revision 2 of the SSID that are listed in 
Section 7, ``SSI Limitation List,'' of the SSID [for airplanes that 
are currently being inspected in accordance with paragraph (a) of 
this AD], or Revision 2 of the SSID [for airplanes that are 
currently being inspected in accordance with paragraph (b) of this 
AD]: Inspect at intervals not to exceed the interval specified for 
each SSI, in accordance with the values given in Section 7, ``SSI 
Limitation List,'' of the SSID or Revision 2 of the SSID, as 
applicable.
    (l) For all airplanes: All inspection results, positive or 
negative, must be reported to Airbus Industrie in accordance with 
either paragraph (l)(1) or (l)(2) of this AD, as applicable. 
Information collection requirements contained in this regulation 
have been approved by the Office of Management and Budget (OMB) 
under the provisions of the Paperwork Reduction Act of 1980 (44 
U.S.C. 3501 et seq.) and have been assigned OMB Control Number 2120-
0056.
    (1) For FLP airplanes, identified in Section 5, ``Fleet Leader 
Program,'' of the SSID or Revision 2 of the SSID: Submit reports in 
accordance with the instructions in paragraph 5.2, ``SSIP Inspection 
Reporting,'' of Section 5, and paragraph 7.1, ``General,'' of 
Section 7 of the SSID [for airplanes that are currently being 
inspected in accordance with paragraph (a) of this AD]; or Revision 
2 of the SSID [for airplanes inspected in accordance with paragraph 
(b) of this AD].
    (2) For all airplanes that are subject to Section 6, ``SB 
Reference List,'' of the SSID: Submit reports in accordance with the 
instructions in the applicable service bulletins identified in 
Section 6 of the SSID [for airplanes that are currently being 
inspected in accordance with paragraph (a) of this AD]; or Revision 
2 of the SSID [for airplanes that are currently being inspected in 
accordance with paragraph (b) of this AD].
    (m) 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 5: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 

[[Page 3346]]
obtained from the Standardization Branch, ANM-113.

    Note 6: Alternative methods of compliance previously granted for 
AD 93-01-24, amendment 39-8478, continue to be considered as 
acceptable alternative methods of compliance with this amendment.

    (n) 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.

    Issued in Renton, Washington, on January 25, 1996.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 96-1874 Filed 1-30-96; 8:45 am]
BILLING CODE 4910-13-M