AD 2001-03-14

[Federal Register Volume 66, Number 35 (Wednesday, February 21, 2001)]
[Rules and Regulations]
[Pages 10957-10960]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 01-3852]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-47-AD; Amendment 39-12118; AD 2001-03-14]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 B4 Series Airplanes, 
and Model A300 B4-600, A300 B4-600R, and A300 F4-600R (Collectively 
Called A300-600) Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain Airbus Model A300 series airplanes and all Airbus 
Model A300-600 series airplanes, that requires 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 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 splice

[[Page 10958]]

fitting at fuselage FR 47, which could result in reduced structural 
integrity of the airplane.

DATES: Effective March 28, 2001.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of March 28, 2001.

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, 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) to include an airworthiness 
directive (AD) that is applicable to certain Airbus Model A300 series 
airplanes and all Airbus Model A300-600 series airplanes was published 
in the Federal Register on April 5, 2000 (65 FR 17822). That action 
proposed to require a one-time high frequency eddy current (HFEC) 
inspection to detect cracking of the splice fitting at fuselage frame 
(FR) 47 between stringers 24 and 25, and corrective actions, if 
necessary.

Comments Received

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.

Airplane Model Designation and Change in AD Applicability

    Since the issuance of the proposed AD, the FAA has determined that 
it is necessary to revise the manner in which it specifies the model 
designation for Airbus Model A300 and A300-600 series airplanes to 
reflect the designations that appear on the type certificate data sheet 
(TCDS). This final rule has been revised accordingly.
    Additionally, an incorrect reference to Model A300 F4-200 series 
airplanes has been removed from paragraph (a)(2) of this final rule 
since that airplane model has not been type certificated in the United 
States.
    Further, since the issuance of the proposed AD, the FAA also has 
determined that the applicability was stated incorrectly in the 
proposal. Airbus Model A300 B2K-3C airplanes were inadvertently 
included in the applicability of the proposed AD. Reference to that 
model has been removed from the applicability of this final rule.
    In addition, the applicability of the proposed AD indicates that 
``All Model A300-600 series airplanes'' and that ``Model * * * A300 B4-
600, A300 B4-600R, and A300 F4-600R series airplanes on which Airbus 
Modification 5890 (Airbus Service Bulletin A300-53-0199) has been 
installed'' are among the affected airplanes. However, Model A300 B4-
600, A300 B4-600R, and A300 F4-600R series airplanes, which are 
commonly referred to as ``Model A300-600 series airplanes,'' were 
mistakenly associated in the applicability of the proposed AD with 
Model A300 series airplanes on which Modification 5890 has been 
incorporated. The parallel French airworthiness directive 1999-515-
298(B), dated December 29, 1999, indicates that all Model A300-600 
series airplanes are affected. The FAA intended to mirror the 
applicability of the French airworthiness directive in the 
applicability of the proposed AD. Therefore, the applicability of this 
final rule has been revised to reflect the affected models as shown in 
the French airworthiness directive.

Request to Allow Flight with Cracks

    One commenter, Airbus, requests that the proposed AD be revised to 
provide a 100-flight-cycle grace period for splice replacement under 
certain conditions. That is, this grace period would allow flight with 
cracks in the area from hole A to the edge, provided that inspection of 
the area between holes A and J reveals no cracks. Airbus states that 
flight with such cracks was allowed by the Direction Generale de 
l'Aviation Civile (DGAC), which is the airworthiness authority for 
France, in its parallel French airworthiness directive for the 
following reasons. The commenter notes that its statements are 
justified in two technical notes and in a laboratory report.
    There are three stages of crack propagation of the splice that 
occur in the following sequence:
    <bullet> From hole A to the edge;
    <bullet> Between hole A and hole J (hole B in the laboratory 
report);
    <bullet> From hole J to failure of the splice (the duration of this 
phase is 1,600 flight cycles).
    The first inspection specified in the All Operators Telex (AOT) is 
accomplished to detect cracks from hole A to the edge. If a crack is 
found, then an inspection is performed between holes A and J. If no 
crack is found between holes A and J, then a grace period of 100 flight 
cycles is given for splice replacement. Since the measured crack 
propagation from hole J to splice failure is 1,600 flight cycles (as 
measured on the airplane having manufacturer's serial number 255), it 
is conservative to allow 100 flight cycles as a grace period for splice 
replacement. In addition, the structure can still sustain ultimate 
loads with the splice failed and limit loads with the splice plus frame 
failed. The 100-flight-cycle grace period is provided to allow 
operators to get a spare splice and plan the work.
    The FAA concurs with the commenter's request to provide a 100-
flight-cycle grace period for splice replacement under certain 
conditions, as specified in the referenced AOT's. While it is not the 
FAA's normal policy to allow flight with known cracks, in light of the 
technical data submitted by the manufacturer in this case, the FAA has 
determined that further flight with cracking in the situation described 
by the commenter can be permitted for the recommended 100-flight-cycle 
grace period. The FAA recognizes the unusual need that exists due to 
the work that is required to replace a splice fitting.
    Further, the FAA finds that the cracks observed are sufficiently 
far from other known crack sites so that existing inspection programs 
can be considered valid independently from one another. In 
consideration of these findings and based on the FAA's criteria for 
flight with known cracking, the FAA has determined that further flight 
with cracking is permissible for a grace period of 100 flight cycles in 
this specific case.
    It should be noted that Airbus specified the 100-flight-cycle grace 
period in the AOT's that are cited in this final rule. Now that the FAA 
is allowing that same grace period, this final rule has been revised to 
more closely parallel the actions and compliance times specified in the 
AOT's with one exception. (That exception involves contacting the FAA, 
rather than the manufacturer, for disposition of certain findings, 
which was explained in the preamble of the proposed AD.) Therefore, the 
FAA has revised the formatting of this final rule to coincide with the 
actions and compliance times specified in the AOT's.

Conclusion

    After careful review of the available data, including the comment 
noted

[[Page 10959]]

above, the FAA has determined that air safety and the public interest 
require the adoption of the rule with the changes described previously. 
The FAA has determined that these changes will neither increase the 
economic burden on any operator nor increase the scope of the AD.

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 will be 
affected by this AD, that it will take approximately 1 work hour per 
airplane to accomplish the required one-time HFEC inspection, and that 
the average labor rate is $60 per work hour. Based on these figures, 
the cost impact of the 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 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 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 final rule does not have federalism 
implications under Executive Order 13132.
    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:

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:

2001-03-14  Airbus Industrie: Amendment 39-12118. Docket 2000-NM-47-
AD.

    Applicability: All Model A300 B4-600, B4-600R, and F4-600R 
(Collectively Called A300-600) series airplanes; and Model A300 B4 
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 and Corrective Actions

    (a) Perform a high frequency eddy current (HFEC) inspection to 
detect cracking of the splice fitting at fuselage FR 47 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. Do the 
inspection at the applicable time specified in paragraph (a)(1), 
(a)(2), (a)(3), or (a)(4) of this AD. Perform applicable corrective 
actions (e.g., removing the nut at hole ``A'' and performing an 
inspection using a shielded probe; replacing the splice fitting with 
a new splice fitting; performing an inspection around fastener holes 
``A'' to ``N'' on the face of FR 47 adjacent to the splice fitting), 
in accordance with and at the times specified in the applicable AOT.

Compliance Times for Inspection of Model A300 Series Airplanes

    (1) For Model A300 B4-100 series airplanes: Perform the 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 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 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 HFEC inspection within 750 
flight cycles after the effective date of this AD.
    (2) For Model A300 B4-200 series airplanes: Perform the 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 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 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 HFEC inspection within 750 flight cycles after the 
effective date of this AD.

Compliance Times for Inspection of Model A300-600 Series Airplanes

    (3) For Model A300-600 series airplanes on which Airbus 
Modification 5890 is not installed: Perform the 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 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 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 HFEC 
inspection within 500 flight cycles after the effective date of this 
AD.

[[Page 10960]]

    (4) For Model A300-600 series airplanes on which Airbus 
Modification 5890 is installed: Perform the 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 HFEC 
inspection within 500 flight cycles after the effective date of this 
AD.

Disposition of Certain Crack Findings

    (b) Where Airbus AOT A300-53A0350 (for Model A300 series 
airplanes) or A300-600-53A6123 (for Model A300-600 series 
airplanes), both dated October 25, 1999, specifies to contact Airbus 
in case of certain crack findings, this AD requires that a repair be 
accomplished 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 
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.

Incorporation by Reference

    (e) Except as required by paragraph (b) of this AD, the actions 
shall be done in accordance with Airbus All Operators Telex A300-
53A0350, dated October 25, 1999; or Airbus All Operators Telex A300-
600-53A6123, dated October 25, 1999; as applicable. This 
incorporation by reference was approved by the Director of the 
Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 
51. 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 3: The subject of this AD is addressed in French 
airworthiness directive 1999-515-298(B), dated December 29, 1999.

Effective Date

    (f) This amendment becomes effective on March 28, 2001.

    Issued in Renton, Washington, on February 9, 2001.
Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-3852 Filed 2-20-01; 8:45 am]
BILLING CODE 4910-13-P