[Federal Register Volume 65, Number 197 (Wednesday, October 11, 2000)]
[Rules and Regulations]
[Pages 60349-60351]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-25533]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-207-AD; Amendment 39-11926; AD 2000-20-15]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 and 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 and A300-600 series airplanes, 
that requires a high frequency eddy current (HFEC) inspection to detect 
cracking of the rear fittings of fuselage frame FR40 at stringer 27, 
and repetitive inspections or repair, as applicable. In lieu of 
accomplishing the repetitive inspections, this amendment requires a 
modification that would allow the inspection to be deferred for a 
certain period of time. 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 fatigue cracking of the rear fittings of fuselage 
frame FR40 at stringer 27, which could result in reduced structural 
integrity of the airplane.

DATES: Effective November 15, 2000.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of November 15, 2000.

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) to include an airworthiness 
directive (AD) that is applicable to certain Airbus Model A300 and 
A300-600 series airplanes was published in the Federal Register on May 
10, 2000 (65 FR 30033). That action proposed to require a high 
frequency eddy current (HFEC) inspection to detect cracking of the rear 
fittings of fuselage frame FR40 at stringer 27, and repetitive 
inspections or repair, as applicable. In lieu of accomplishing the 
repetitive inspections, that action proposed to require a modification 
that would allow the inspection to be deferred for a certain period of 
time.

Comment Received

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

Request To Revise Compliance Times

    The commenter questions the compliance times specified in the 
proposed AD. The commenter notes that there are small discrepancies 
between the compliance thresholds recommended in the referenced service 
bulletins for Airbus Model A300 B2, B4-100, and B4-600 series 
airplanes, and the thresholds specified by the proposed AD. The 
commenter suggests that it would be preferable for the compliance times 
in the AD to be in line with those in the service bulletins, since this 
would avoid confusion by operators and reduce the number of questions 
that may be raised.
    The FAA concurs. For the reasons stated in the proposed AD, the FAA 
specified fixed compliance times for accomplishment of the required 
actions, rather than permitting use of the ``adjustment-for-range'' 
formula for calculating compliance times. During discussions with the 
manufacturer to determine an interim method of calculating the fixed 
compliance times, flight cycle thresholds and intervals for certain 
models were recommended for reduction from those in the service 
bulletins, based on the average flight times of those models. 
Subsequently, a revised method for calculation of such fixed compliance 
times was defined by the manufacturer. This method allows use of the 
flight cycle thresholds and intervals specified in the referenced 
service bulletins.
    The FAA has determined that, consistent with the manufacturer's 
revised method for calculation of fixed compliance times, the flight 
cycle thresholds and intervals recommended in the referenced service 
bulletins constitute acceptable compliance times for this AD. The final 
rule has been

[[Page 60350]]

revised accordingly. Because the flight cycle compliance times for 
certain airplane models have been increased rather than reduced, and 
the flight hour compliance times are unchanged, such revision imposes 
no additional restrictions on operators.

Conclusion

    After careful review of the available data, including the comment 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule with the change described 
previously. The FAA has determined that this change will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.

Cost Impact

    The FAA estimates that 85 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 HFEC inspection, and that the 
average labor rate is $60 per work hour. Based on these figures, the 
cost impact of the inspection on U.S. operators is estimated to be 
$5,100, or $60 per airplane, per inspection cycle.
    Should an operator be required to accomplish the modification 
rather than the repetitive inspections, it will take approximately 3 
work hours per airplane to accomplish. Based on these figures, the cost 
impact of the modification required by this AD on U.S. operators is 
estimated to be $15,300, or $180 per airplane.
    The cost impact figures discussed above are 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. The cost impact figures discussed 
in AD rulemaking actions represent only the time necessary to perform 
the specific actions actually required by the AD. These figures 
typically do not include incidental costs, such as the time required to 
gain access and close up, planning time, or time necessitated by other 
administrative actions.

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:

2000-20-15  Airbus Industrie: Amendment 39-11926. Docket 98-NM-207-
AD.

    Applicability: Model A300 and A300-600 series airplanes, on 
which Airbus Modification 11525 has not been accomplished; 
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 (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 fatigue cracking of the rear fittings of 
fuselage frame FR40 at stringer 27, which could result in reduced 
structural integrity of the airplane, accomplish the following:

Inspection

    (a) Perform a high frequency eddy current (HFEC) inspection to 
detect cracks in the stiffeners at stringer 27 of the rear fitting 
of fuselage frame FR40, left and right, in accordance with Airbus 
Service Bulletin A300-53-0332, dated November 24, 1997 (for Model 
A300 B2 and B4 series airplanes), or Airbus Service Bulletin A300-
57-6075, dated November 24, 1997 (for Model A300-600 series 
airplanes); as applicable; at the applicable time specified in 
paragraph (a)(1), (a)(2), (a)(3), (a)(4), (a)(5), (a)(6), (a)(7), or 
(a)(8) of this AD.
    (1) For Model A300 B2 series airplanes that have accumulated 
less than 26,000 total flight cycles as of the effective date of 
this AD: Inspect at the earlier of the times specified in paragraphs 
(a)(1)(i) and (a)(1)(ii) of this AD.
    (i) Prior to the accumulation of 11,600 total flight cycles, or 
within 3,000 flight cycles after the effective date of this AD, 
whichever occurs later.
    (ii) Prior to the accumulation of 14,300 total flight hours, or 
within 3,800 flight hours after the effective date of this AD, 
whichever occurs later.
    (2) For Model A300 B2 series airplanes that have accumulated 
26,000 or more total flight cycles as of the effective date of this 
AD: Inspect within 2,200 flight cycles or 2,800 flight hours after 
the effective date of this AD, whichever occurs first.
    (3) For Model A300 B4-100 series airplanes that have accumulated 
less than 20,000 total flight cycles as of the effective date of 
this AD: Inspect at the earlier of the times specified in paragraphs 
(a)(3)(i) and (a)(3)(ii) of this AD.
    (i) Prior to the accumulation of 9,200 total flight cycles, or 
within 3,000 flight cycles after the effective date of this AD, 
whichever occurs later.
    (ii) Prior to the accumulation of 15,700 total flight hours, or 
within 5,800 flight hours after the effective date of this AD, 
whichever occurs later.
    (4) For Model A300 B4-100 series airplanes that have accumulated 
20,000 or more total flight cycles as of the effective date of this 
AD: Inspect within 1,800 flight cycles or 3,400 flight hours after 
the effective date of this AD, whichever occurs first.
    (5) For Model A300 B4-200 series airplanes that have accumulated 
less than 14,000 total flight cycles as of the effective date of 
this AD: Inspect at the earlier of the times specified in paragraphs 
(a)(5)(i) and (a)(5)(ii) of this AD.
    (i) Prior to the accumulation of 8,300 total flight cycles, or 
within 3,000 flight cycles after the effective date of this AD, 
whichever occurs later.
    (ii) Prior to the accumulation of 17,200 total flight hours, or 
within 6,200 flight hours after the effective date of this AD, 
whichever occurs later.
    (6) For Model A300 B4-200 series airplanes that have accumulated 
14,000 or more total flight cycles as of the effective date of this 
AD: Inspect within 1,700 flight cycles or 3,500 flight hours after 
the effective date of this AD, whichever occurs first.

[[Page 60351]]

    (7) For Model A300-600 series airplanes that have accumulated 
less than 18,000 total flight cycles as of the effective date of 
this AD: Inspect at the earlier of the times specified in paragraphs 
(a)(7)(i) and (a)(7)(ii) of this AD.
    (i) Prior to the accumulation of 6,200 total flight cycles, or 
within 2,700 flight cycles after the effective date of this AD, 
whichever occurs later.
    (ii) Prior to the accumulation of 15,100 total flight hours, or 
within 7,000 flight hours after the effective date of this AD, 
whichever occurs later.
    (8) For Model A300-600 series airplanes that have accumulated 
18,000 or more total flight cycles as of the effective date of this 
AD: Inspect within 1,400 flight cycles or 3,600 flight hours after 
the effective date of this AD, whichever occurs first.

Repetitive Inspections

    (b) If no crack is detected during the initial inspection 
required by paragraph (a) of this AD, except as provided by 
paragraph (e) of this AD, repeat the inspection required by 
paragraph (a) of this AD at the time specified in paragraph (b)(1), 
(b)(2), (b)(3), or (b)(4) of this AD, as applicable.
    (1) For Model A300 B2 series airplanes: Repeat at intervals not 
to exceed 2,200 flight cycles or 2,700 flight hours, whichever 
occurs first.
    (2) For Model A300 B4-100 series airplanes: Repeat at intervals 
not to exceed 1,800 flight cycles or 3,000 flight hours, whichever 
occurs first.
    (3) For Model A300 B4-200 series airplanes: Repeat at intervals 
not to exceed 1,700 flight cycles or 3,500 flight hours, whichever 
occurs first.
    (4) For Model A300-600 series airplanes: Repeat at intervals not 
to exceed 1,400 flight cycles or 3,400 flight hours, whichever 
occurs first.

Repair Cracking Found During Inspections

    (c) If any crack is found during any inspection required by 
paragraph (a) or (b) of this AD and the crack is less than 0.787 
inches long, prior to further flight, repair in accordance with 
Airbus Service Bulletin A300-53-0332, dated November 24, 1997 (for 
Model A300 B2 and B4 series airplanes), or Airbus Service Bulletin 
A300-57-6075, dated November 24, 1997 (for Model A300-600 series 
airplanes); as applicable. Perform the inspection required by 
paragraph (a) of this AD one more time at the time specified in 
paragraph (c)(1), (c)(2), (c)(3), or (c)(4) of this AD, as 
applicable, and accomplish the actions specified in paragraph (f) or 
(g) of this AD, as applicable.
    (1) For Model A300 B2 series airplanes: Within 44,500 flight 
cycles or 54,600 flight hours after accomplishment of the repair, 
whichever occurs first.
    (2) For Model A300 B4-100 series airplanes: Within 35,200 flight 
cycles or 56,700 flight hours after accomplishment of the repair, 
whichever occurs first.
    (3) For Model A300 B4-200 series airplanes: Within 31,900 flight 
cycles or 66,100 flight hours after accomplishment of the repair, 
whichever occurs first.
    (4) For Model A300-600 series airplanes: Within 23,700 flight 
cycles or 57,500 flight hours after accomplishment of the repair, 
whichever occurs first.
    (d) If any crack is found during any inspection required by 
paragraph (a) or (b) of this AD and the crack is 0.787 inches long 
or more, prior to further flight, repair it in accordance with a 
method approved by 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.

Deferral of Repetitive Inspections by Modification

    (e) In lieu of accomplishing the requirements of paragraph (b) 
of this AD, prior to further flight after accomplishing the 
inspection required by paragraph (a) of this AD, modify the rear 
fitting at stringer 27 at FR40 of the center fuselage in accordance 
with Airbus Service Bulletin A300-53-0333, dated November 24, 1997 
(Model A300 B2 and B4 series airplanes), or Airbus Service Bulletin 
A300-57-6076, dated November 24, 1997 (for Model A300-600 series 
airplanes); as applicable. Following accomplishment of the 
modification, perform the inspection required by paragraph (a) of 
this AD one more time at the time specified in paragraph (e)(1), 
(e)(2), (e)(3), or (e)(4) of this AD, as applicable, and accomplish 
the actions specified in paragraph (f) or (g) of this AD, as 
applicable.
    (1) For Model A300 B2 series airplanes: Within 59,600 flight 
cycles or 73,100 flight hours after accomplishment of the 
modification, whichever occurs first.
    (2) For Model A300 B4-100 series airplanes: Within 47,100 flight 
cycles or 75,900 flight hours after accomplishment of the 
modification, whichever occurs first.
    (3) For Model A300 B4-200 series airplanes: Within 42,700 flight 
cycles or 88,400 flight hours after accomplishment of the 
modification, whichever occurs first.
    (4) For Model A300-600 series airplanes: Within 31,700 flight 
cycles or 76,800 flight hours after accomplishment of the 
modification, whichever occurs first.

Follow-on Action if No Cracking Is Found During Certain Inspections

    (f) If no crack is detected during the inspection required by 
paragraph (c) or (e) of this AD, prior to further flight, contact 
the Manager, International Branch, ANM-116, or the DGAC (or its 
delegated agent) for the next inspection time(s), and repeat the 
inspection(s) thereafter at those times.

Repair for Cracking Found During a Certain Inspection

    (g) If any crack is detected during the inspection required by 
paragraph (c) or (e) of this AD, prior to further flight, repair it 
in accordance with a method approved by the Manager, International 
Branch, ANM-116, or the 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

    (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 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

    (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.

Incorporation by Reference

    (j) Except as required by paragraphs (d), (f), and (g) of this 
AD, the actions shall be done in accordance with Airbus Service 
Bulletin A300-53-0332, dated November 24, 1997; Airbus Service 
Bulletin A300-57-6075, dated November 24, 1997; Airbus Service 
Bulletin A300-53-0333, dated November 24, 1997; or Airbus Service 
Bulletin A300-57-6076, dated November 24, 1997; 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 98-028-242 (B), dated January 28, 1998.

    (k) This amendment becomes effective on November 15, 2000.

    Issued in Renton, Washington, on September 29, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-25533 Filed 10-10-00; 8:45 am]
BILLING CODE 4910-13-P