[Federal Register Volume 63, Number 49 (Friday, March 13, 1998)]
[Rules and Regulations]
[Pages 12401-12403]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-6333]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 95-NM-278-AD; Amendment 39-10385; AD 98-06-08]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300, A310, and A300-600 
Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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[[Page 12402]]

SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain Airbus Model A300, A310, and A300-600 series 
airplanes, that requires inspections to detect defects of the flanges 
of the bleed air ducts of the auxiliary power unit (APU), and to 
measure the material thickness of the flanges; and repair, replacement 
of the duct with a new or serviceable duct, or operation of the 
airplane with the bleed air system of the APU inoperative, if 
necessary. For certain airplanes, the amendment also requires an 
inspection to detect cracks of the flanges, and follow-on actions. This 
amendment is prompted by issuance of mandatory continued airworthiness 
information by a foreign civil airworthiness authority. The actions 
specified by this AD are intended to prevent rupturing and cracking of 
the flanges of the bleed air ducts, which could damage the elevator 
control system and consequently reduce the controllability of the 
airplane.

DATES: Effective April 17, 1998.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of April 17, 1998.

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, A310, 
and A300-600 series airplanes was published in the Federal Register on 
January 8, 1998 (63 FR 1070). That action proposed to require 
inspections to detect defects of the flanges of the bleed air ducts of 
the auxiliary power unit (APU), and to measure the material thickness 
of the flanges; and repair, replacement of the duct with a new or 
serviceable duct, or operation of the airplane with the bleed air 
system of the APU inoperative, if necessary. For certain airplanes, the 
action also proposed to require an inspection to detect cracks of the 
flanges, and follow-on actions.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were submitted in response 
to the proposal or the FAA's determination of the cost to the public.

Conclusion

    The FAA has determined that air safety and the public interest 
require the adoption of the rule as proposed.

Cost Impact

    The FAA estimates that 84 airplanes of U.S. registry will be 
affected by this AD, that it will take approximately 9 work hours per 
airplane to accomplish the required actions, 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 $45,360, or $540 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 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 final 
rule does not have sufficient federalism implications to warrant the 
preparation of a Federalism Assessment.
    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, theFederal Aviation Administration amends part 39 of the 
Federal Aviation Regulations (14CFR 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:

98-06-08  Airbus: Amendment 39-10385. Docket 95-NM-278-AD.

    Applicability: Model A300, A310, and A300-600 series airplanes 
on which Airbus Modification 11308 has not been accomplished during 
manufacture; 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 (b) 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 prevent rupturing and cracking of the flanges of the bleed 
air ducts of the auxiliary power unit (APU), and cracking of the 
adjacent duct, which could damage the elevator control system and 
consequently reduce the controllability of the airplane; accomplish 
the following:
    (a) Prior to the accumulation of 5,000 total flight cycles, or 
within 500 flight cycles after the effective date of this AD, 
whichever occurs later: Perform a visual inspection to detect 
defects (recesses, sharp edges, or scratches) of the inner and outer 
surfaces of all flanges of the bleed air ducts of the APU between 
frames 83 and 93 (for Model A300 series airplanes) or between frames 
85 and 93 (for Model A310 and A300-600 series airplanes), as 
applicable, and measure the material thickness of the flanges; in 
accordance with Airbus Service Bulletin A300-36-0033 (for Model A300 
series airplanes), A300-36-6024 (for Model A300-600 series 
airplanes), or A310-36-2032(for

[[Page 12403]]

Model A310 series airplanes), all dated October 17, 1994; as 
applicable. If any defect is found, prior to further flight, repair 
the defect in accordance with the applicable service bulletin.
    (1) If the material thickness of the flanges is within the 
limits [Area 1: greater than or equal to 0.56 mm (0.022 inch); Area 
2: greater than or equal to 0.48 mm (0.019 inch)] specified in 
Airbus Service Bulletin A300-36-0033 (for Model A300 series 
airplanes), A300-36-6024 (for Model A300-600 series airplanes), or 
A310-36-2032 (for Model A310 series airplanes), all dated October 
17, 1994; as applicable: Prior to further flight, perform an 
inspection using a magnifying glass or appropriate gauge to detect 
cracks of the inner and outer surfaces of the flanges, in accordance 
with the applicable service bulletin.
    (i) If no crack is found, and the material thickness of all 
flanges is within the limits [Area 1: greater than or equal to 0.9 
mm (0.035 inch)] specified in the applicable service bulletin: No 
further action is required by this AD.
    (ii) If no crack is found, and the material thickness of any 
flange is outside the limits [Area 1: less than 0.9 mm (0.035 inch)] 
specified in the applicable service bulletin: Repeat the inspection 
required by paragraph (a) of this AD at the time specified in the 
applicable service bulletin.
    (iii) If any crack is found: Prior to further flight, accomplish 
either paragraph(a)(1)(iii)(A) or (a)(1)(iii)(B) of this AD.
    (A) Replace the duct with a new or serviceable duct in 
accordance with the applicable service bulletin. Or
    (B) Operate the airplane with the bleed air system of the APU 
inoperative, in accordance with the provisions and limitations 
specified in the operator's FAA-approvedMaster Minimum Equipment 
List (MMEL).
    (2) If the material thickness of any flange is outside the 
limits [Area 1: less than 0.56 mm (0.022 inch); Area 2: less than 
0.48 mm (0.019 inch)] specified in AirbusService Bulletin A300-36-
0033 (for Model A300 series airplanes), A300-36-6024 (forModel A300-
600 series airplanes), and A310-36-2032 (for Model A310 series 
airplanes), all dated October 17, 1994; as applicable: Prior to 
further flight, accomplish either paragraph (a)(1)(iii)(A) or 
(a)(1)(iii)(B) of this AD.
    (b) 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, FAA, 
Transport Airplane Directorate. 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.

    (c) 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.
    (d) The actions shall be done in accordance with All Operator 
Telex (AOT) 36-02, dated August 23, 1995; Airbus Service Bulletin 
A300-36-0033, dated October 17, 1994; Airbus Service Bulletin A300-
36-6024, dated October 17, 1994; and Airbus Service Bulletin A310-
36-2032, dated October 17, 1994. 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 95-182-184(B), dated September 27, 1995.

    (e) This amendment becomes effective on April 17, 1998.

    Issued in Renton, Washington, on March 5, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-6333 Filed 3-12-98; 8:45 am]
BILLING CODE 4910-13-U