[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]
-----------------------------------------------------------------------
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.
-----------------------------------------------------------------------
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]
BILLING CODE 4910-13-P