[Federal Register Volume 63, Number 183 (Tuesday, September 22, 1998)]
[Rules and Regulations]
[Pages 50511-50512]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-25147]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97-NM-307-AD; Amendment 39-10788; AD 98-20-22]
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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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to all Airbus Model A300, A310, and A300-600 series 
airplanes, that requires repetitive visual inspections to detect 
cracked or broken door stop fittings on the fuselage frame of the 
forward passenger doors, and replacement of any cracked or broken 
fitting with a new fitting. 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 cracked or broken door stop fittings of the 
forward passenger doors, which could result in failure of the door stop 
fittings, consequent reduced structural integrity of the door support 
structure, and sudden loss of cabin pressure in the passenger 
compartment.

DATES: Effective October 27, 1998.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of October 27, 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 all Airbus Model A300, A310, and 
A300-600 series airplanes was published in the Federal Register on July 
7, 1998 (63 FR 36622). That action proposed to require repetitive 
visual inspections to detect cracked or broken door stop fittings on 
the fuselage frame of the forward passenger doors, and replacement of 
any cracked or broken fitting with a new fitting.

Comments 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 Delete Proposed Immediate Replacement Requirement

    One commenter requests that the FAA delete the requirement for 
immediate replacement of cracked or broken fittings [as required by 
paragraph (b) of the proposed AD]. The commenter states that the Master 
Minimum Equipment List (MMEL) compliance times referenced in Airbus 
Service Bulletin A300-53-6060 would be sufficient, since Airbus reports 
of single findings are rare. The commenter also states that it is not 
reasonable for the FAA to assume that a large number of fittings are on 
the verge of failure. The commenter states that allowing aircraft to 
operate under MMEL compliance times will enable it to schedule repairs 
in a manner which minimizes operational impact.
    The FAA does not concur with the commenter's request to delete the 
requirement for immediate replacement of any cracked or broken door 
stop fittings. It is the FAA's policy to require repair of known cracks 
prior to further flight (except in certain cases of unusual need). This 
policy is based on the fact that such damaged airplanes do not conform 
to the FAA certificated type design, and therefore, are not airworthy 
until a properly approved repair is incorporated. Further, the FAA 
considers that deferral of the compliance time for accomplishment of 
repairs, as specified in the MMEL, is not appropriate in this case, 
since to accomplish the inspection the airplane would already be at a 
location where such repairs can be made. Therefore, such repairs would 
be expected to have a minimal impact on operation of the airplane. No 
change to the final rule is necessary.

Conclusion

    After careful review of the available data, including the comments 
noted above, 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 103 Model A300, A310, and A300-600 series 
airplanes of U.S. registry will be affected by this AD, that it will 
take approximately 2 work hours per airplane to accomplish the required 
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 $12,360, or $120 per airplane, per inspection cycle.
    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.

[[Page 50512]]

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:

98-20-22  Airbus Industrie: Amendment 39-10788. Docket 97-NM-307-AD.

    Applicability: All Model A300, A310, and A300-600 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 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 cracked or broken door stop fittings of 
the forward passenger doors, which could result in failure of the 
door stop fittings, consequent reduced structural integrity of the 
door support structure, and sudden loss of cabin pressure in the 
passenger compartment, accomplish the following:
    (a) Prior to the accumulation of the total flight cycles 
specified in the ``Threshold'' column of paragraph 1.B.(5) of the 
Planning Information of Airbus Service Bulletin A300-53-0309 (for 
Model A300 series airplanes); A310-53-2087 (for Model A310 series 
airplanes); or A300-53-6060 (for Model A300-600 series airplanes); 
all dated March 19, 1997; as applicable; or within 200 flight cycles 
after the effective date of this AD, whichever occurs later; 
accomplish paragraphs (a)(1) and (a)(2) of this AD.
    (1) Perform a visual inspection of the left and right forward 
passenger door stop fittings to detect cracked or broken door stop 
fittings, in accordance with the applicable service bulletin.
    (2) Thereafter, repeat the visual inspection at the intervals 
specified in the ``Intervals'' column of paragraph 1.B.(5) of the 
Planning Information of the applicable service bulletin.
    (b) If any cracked or broken door stop fitting is detected 
during any inspection required by paragraph (a)(1) or (a)(2) of this 
AD, prior to further flight, replace the door stop fitting with a 
new fitting in accordance with Airbus Service Bulletin A300-53-0309 
(for Model A300 series airplanes); A310-53-2087 (for Model A310 
series airplanes); or A300-53-6060 (for Model A300-600 series 
airplanes); all dated March 19, 1997; as applicable. Thereafter, 
repeat the visual inspections at the intervals specified in the 
``Intervals'' column of paragraph 1.B.(5) of the Planning 
Information of the applicable service bulletin.
    (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, 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.

    (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.
    (e) The actions shall be done in accordance with Airbus Service 
Bulletin A300-53-0309, dated March 19, 1997; Airbus Service Bulletin 
A310-53-2087, dated March 19, 1997; or Airbus Service Bulletin A300-
53-6060, dated March 19, 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 97-124-223(B), dated June 4, 1997.

    (f) This amendment becomes effective on October 27, 1998.

    Issued in Renton, Washington, on September 15, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-25147 Filed 9-21-98; 8:45 am]
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