[Federal Register Volume 65, Number 66 (Wednesday, April 5, 2000)]
[Proposed Rules]
[Pages 17822-17824]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-8389]



[[Page 17822]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-47-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 and A300-600 Series 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the adoption of a new airworthiness 
directive (AD) that is applicable to certain Airbus Model A300 series 
airplanes and all Airbus Model A300-600 series airplanes. This proposal 
would require a one-time high frequency eddy current inspection to 
detect cracking of the splice fitting at fuselage frame (FR) 47 between 
stringers 24 and 25, and corrective actions, 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 splice fitting at fuselage FR47, which could result in 
reduced structural integrity of the airplane.

DATES: Comments must be received by May 5, 2000.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2000-NM-47-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, 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 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 2000-NM-47-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. 2000-NM-47-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    The Direction Generale de l'Aviation Civile (DGAC), which is the 
airworthiness authority for France, notified the FAA that an unsafe 
condition may exist on certain Airbus Model A300 series airplanes and 
all Airbus Model A300-600 series airplanes. The DGAC advises that it 
has received reports indicating that cracking occurred in the area 
surrounding the fastener holes that attach the splice fitting to 
fuselage frame (FR) 47 on airplanes on which Airbus Modification 5890 
had been installed. This modification specifies cold working of the 
fastener holes in the splice fitting at fuselage FR47. As a result of a 
laboratory analysis of the cracked splice fittings, the DGAC further 
advises that inspection of all subject airplanes to detect cracking of 
the splice fitting at fuselage FR47 is necessary, regardless of whether 
the modification is installed. Such cracking, if not detected and 
corrected, could result in reduced structural integrity of the 
airplane.

Explanation of Relevant Service Information

    The manufacturer has issued Airbus All Operators Telexes (AOT) 
A300-53A0350 (for Model A300 series airplanes) and A300-600-53A6123 
(for Model A300-600 series airplanes), both dated October 25, 1999. 
These AOT's describe procedures for a one-time high frequency eddy 
current (HFEC) inspection to detect cracking of the splice fitting at 
fuselage FR47 between stringers 24 and 25, and corrective actions, if 
necessary. The corrective actions involve additional HFEC inspections 
to determine whether any cracking extends beyond fastener ``A'' of the 
splice fitting at fuselage FR47 and to detect cracking in the area 
surrounding the fastener holes of the splice fitting on the face of 
FR47. If cracking is determined to extend beyond fastener `A', but is 
not detected in the area surrounding the fastener holes, the corrective 
actions involve replacing the splice fitting with a new splice fitting. 
The DGAC classified these AOT's as mandatory and issued French 
airworthiness directive 1999-515-298(B), dated December 29, 1999, in 
order to assure the continued airworthiness of these airplanes in 
France.

FAA's Conclusions

    These airplane models are manufactured in France and are 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 require a one-time high 
frequency eddy current inspection to detect cracking of the splice 
fitting at fuselage FR47 between stringers 24 and 25, and corrective 
actions, if necessary. The actions would

[[Page 17823]]

be required to be accomplished in accordance with the AOT's described 
previously, except as discussed below.

Differences Between Proposed AD and Related Service Information

    Operators should note that, although the Airbus AOT's specify that 
the manufacturer may be contacted for disposition of certain 
conditions, this proposal would require the repair of those conditions 
to be accomplished in accordance with a method approved by either the 
FAA or the DGAC (or its delegated agent). In light of the type of 
repair that would be required to address the identified unsafe 
condition, and in consonance with existing bilateral airworthiness 
agreements, the FAA has determined that, for the proposed AD, a repair 
approved by either the FAA or the DGAC would be acceptable for 
compliance with this proposed AD.
    The Airbus AOT's describe procedures for an additional HFEC 
inspection, which under certain circumstances allows operators to defer 
replacement of the splice fitting. This proposed AD would not require 
this inspection. Unlike the procedures described in the Airbus AOT's, 
this proposed AD would not permit further flight if cracks are detected 
in the splice fitting at fuselage FR47. The FAA has determined that, 
because of the safety implications and consequences associated with 
such cracking, any subject area that is found to be cracked must be 
repaired or modified prior to further flight.

Interim Action

    This is considered to be interim action until final action is 
identified, at which time the FAA may consider further rulemaking.

Cost Impact

    The FAA estimates that 83 airplanes of U.S. registry would be 
affected by this proposed AD, that it would take approximately 1 work 
hour per airplane to accomplish the proposed one-time HFEC inspection, 
and that the average labor rate is $60 per work hour. Based on these 
figures, the cost impact of the proposed AD on U.S. operators is 
estimated to be $4,980, or $60 per airplane.
    The cost impact figure discussed above is 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 a substantial direct 
effect 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, it 
is determined that this proposal would not have federalism implications 
under Executive Order 13132.
    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 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 adding the following new 
airworthiness directive:

Airbus Industrie: Docket 2000-NM-47-AD.

    Applicability: All Model A300-600 series airplanes; and Model 
A300B4-2C, A300B2K-3C, A300B4-103, A300B4-203, A300B4-600, A300B4-
600R, and A300F4-600R series airplanes on which Airbus Modification 
5890 (Airbus Service Bulletin A300-53-0199) has been installed; 
certificated in any category.

    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 (c) 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 splice fitting at fuselage 
frame (FR) 47, which could result in reduced structural integrity of 
the airplane, accomplish the following:

Inspection

    (a) Perform a one-time high frequency eddy current (HFEC) 
inspection to detect cracking of the splice fitting at fuselage FR47 
between stringers 24 and 25 (left-and right-hand sides), in 
accordance with Airbus All Operators Telex (AOT) A300-53A0350 (for 
Model A300 series airplanes) or A300-600-53A6123 (for Model A300-600 
series airplanes), both dated October 25, 1999; as applicable; at 
the applicable time specified in paragraph (a)(1), (a)(2), (a)(3), 
or (a)(4) of this AD.

For Model A300 Series Airplanes

    (1) For Model A300 B4-100 series airplanes: Perform the one-time 
HFEC inspection at the applicable time specified in paragraph 
(a)(1)(i) or (a)(1)(ii) of this AD.
    (i) For airplanes that, as of the effective date of this AD, 
have accumulated fewer than 20,000 flight cycles since installation 
of Airbus Modification 5890 (Airbus Service Bulletin A300-53-0199): 
Perform the one-time HFEC inspection at the later of the times 
specified in paragraphs (a)(1)(i)(A) and (a)(1)(i)(B) of this AD.
    (A) Within 10,900 flight cycles or 22,000 flight hours since 
installation of Airbus Modification 5890, whichever occurs earlier.
    (B) Within 1,500 flight cycles after the effective date of this 
AD.
    (ii) For airplanes that, as of the effective date of this AD, 
have accumulated 20,000 or more flight cycles since installation of 
Airbus Modification 5890: Perform the one-time HFEC inspection 
within 750 flight cycles after the effective date of this AD.
    (2) For Model A300B4/F4-200 series airplanes: Perform the one-
time HFEC inspection at the applicable time specified in paragraph 
(a)(2)(i) or (a)(2)(ii) of this AD.
    (i) For airplanes that, as of the effective date of this AD, 
have accumulated fewer than 20,000 flight cycles since installation 
of Airbus Modification 5890 (Airbus Service Bulletin A300-53-0199): 
Perform the one-time HFEC inspection at the later of the times 
specified in paragraphs (a)(2)(i)(A) and (a)(2)(i)(B) of this AD.
    (A) Within 8,950 flight cycles or 18,600 flight hours since 
installation of Airbus Modification 5890, whichever occurs earlier.
    (B) Within 1,500 flight cycles after the effective date of this 
AD.
    (ii) For airplanes that, as of the effective date of this AD, 
have accumulated 20,000 or more flight cycles since installation of 
Airbus Modification 5890 (Airbus Service Bulletin A300-53-0199): 
Perform the one-time HFEC inspection within 750 flight cycles after 
the effective date of this AD.

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For Model A300-600 Series Airplanes

    (3) For Model A300-600 series airplanes on which Airbus 
Modification 5890 is not installed: Perform the one-time HFEC 
inspection at the applicable time specified in paragraph (a)(3)(i) 
or (a)(3)(ii) of this AD.
    (i) For airplanes that have accumulated fewer than 10,000 total 
flight cycles as of the effective date of this AD: Perform the one-
time HFEC inspection at the later of the times specified in 
paragraphs (a)(3)(i)(A) and (a)(3)(i)(B) of this AD.
    (A) Prior to the accumulation of 2,500 total flight cycles or 
6,400 total flight hours, whichever occurs earlier.
    (B) Within 1,500 flight cycles after the effective date of this 
AD.
    (ii) For airplanes that have accumulated 10,000 or more total 
flight cycles as of the effective date of this AD: Perform the one-
time HFEC inspection within 500 flight cycles after the effective 
date of this AD.
    (4) For Model A300-600 series airplanes on which Airbus 
Modification 5890 is installed: Perform the one-time HFEC inspection 
at the applicable time specified in paragraph (a)(4)(i) or 
(a)(4)(ii) of this AD.
    (i) For airplanes that have accumulated fewer than 10,000 total 
flight cycles as of the effective date of this AD: Perform the one-
time HFEC inspection at the later of the times specified in 
paragraph (a)(4)(i)(A) and (a)(4)(i)(B) of this AD.
    (A) Prior to the accumulation of 6,500 total flight cycles or 
16,700 total flight hours, whichever occurs earlier.
    (B) Within 1,500 flight cycles after the effective date of this 
AD.
    (ii) For airplanes that have accumulated 10,000 or more total 
flight cycles as of the effective date of this AD: Perform the one-
time HFEC inspection within 500 flight cycles after the effective 
date of this AD.

Corrective Actions

    (b) If any cracking is detected during the one-time HFEC 
inspection required by paragraph (a) of this AD, prior to further 
flight, remove the splice fitting and perform an HFEC inspection to 
detect cracking in the area surrounding the fastener holes (fastener 
holes ``A'' to ``N'') on the face of FR47 adjacent to the affected 
splice fitting, in accordance with Airbus AOT A300-53A0350 (for 
Model A300 series airplanes) or A300-600-53A6123 (for Model A300-600 
series airplanes), each dated October 25, 1999, as applicable.
    (1) If no cracking is detected in the area surrounding the 
fastener holes on the face of FR47, prior to further flight, replace 
the splice fitting with a new splice fitting in accordance with the 
applicable AOT.
    (2) If any cracking is detected in the area surrounding the 
fastener holes on the face of FR47, prior to further flight, repair 
in accordance with a method approved by either the Manager, 
International Branch, ANM-116, FAA, Transport Airplane Directorate; 
or the Direction Generale de l'Aviation Civile (DGAC) (or its 
delegated agent). For a repair method to be approved by the Manager, 
International Branch, ANM-116, as required by this paragraph, the 
Manager's approval letter must specifically reference this AD.

Alternative Methods of Compliance

    (c) 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 2: 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

    (d) 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.

    Note 3: The subject of this AD is addressed in French 
airworthiness directive 1999-515-298(B), dated December 29, 1999.


    Issued in Renton, Washington, on March 30, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-8389 Filed 4-4-00; 8:45 am]
BILLING CODE 4910-13-U