[Federal Register Volume 63, Number 178 (Tuesday, September 15, 1998)]
[Rules and Regulations]
[Pages 49272-49273]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-24248]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-NM-156-AD; Amdt. 39-10740; AD 98-18-24]
RIN 2120-AA64
Airworthiness Directives; Airbus Industrie Model A320 Series
Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to certain Airbus Model A320 series airplanes, that requires
repetitive inspections to detect cracking in the inner flange of door
frame 66, and corrective actions, if necessary. This amendment also
provides for an optional terminating action for the repetitive
inspections. 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 correct
fatigue cracking in the inner flange of door frame 66, which could
result in reduced structural integrity of the airplane.
DATES: Effective October 20, 1998.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of October 20, 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 A320 series
airplanes was published in the Federal Register on May 12, 1998 (63 FR
26102). That action proposed to require repetitive inspections to
detect cracking in the inner flange of door frame 66, and corrective
actions, if necessary. That action also proposed to provide for an
optional terminating action for the repetitive inspections.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the comments received.
One commenter supports the intent of the proposed rule.
Request To Allow Flight With Known Cracks
One commenter, the manufacturer, requests that the proposed AD be
revised to allow operators to continue operation of an unrepaired
airplane following detection of cracks, utilizing the follow-on
inspections and conditions described in Airbus Service Bulletin A320-
53-1071. The commenter states that the follow-on inspection intervals
are based on fatigue test results and calculations of the crack
propagation rate, depending on the crack length. The commenter also
states that the structure of the Airbus Model A320 series airplane is
classified as damage tolerant. Additionally, the commenter notes that
the inspection program specified in the service bulletin was developed
in order to prevent the need for extensive repairs of the airplane.
The FAA does not concur. It is the FAA's policy to require repair
of known cracks prior to further flight, except in certain cases of
unusual need, as discussed below.
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. While
recognizing that repair deferrals may be necessary at times, the FAA
policy is intended to minimize adverse human factors relating to the
lack of reliability of long-term repetitive inspections, which may
reduce the safety of the type certificated design if such repair
deferrals are practiced routinely.
As noted above, the FAA's policy regarding flight with known cracks
does allow deferral of repairs in certain cases, if there is an unusual
need for a temporary deferral. Unusual needs include such circumstances
as legitimate difficulty in acquiring parts to accomplish repairs.
Under such conditions, the FAA may allow a temporary deferral of the
repair, subject to a stringent inspection program acceptable to the
FAA. The FAA acknowledges that the manufacturer has specified
inspection intervals that are intended to allow continued operation
with known cracks, and to prevent the need for extensive repairs.
However, since the FAA is not aware of any unusual need for repair
deferral in regard to this AD, the FAA has not evaluated these
inspection intervals.
Additionally, the FAA policy applies to airplanes certificated to
damage tolerance evaluation regulations as well as those not so
certificated. Therefore, the commenter's statement that ``the Airbus
Model A320 airplane structure is classified as damage tolerant'' is not
relevant to the application of the FAA's policy in this regard.
The FAA considers the compliance times in this AD to be adequate to
allow operators to acquire parts to have on hand in the event that a
crack is detected during inspection. Therefore, the FAA has determined
that, due to the safety implications and consequences associated with
such cracking, any subject area that is found to be cracked must be
repaired or modified prior to further flight. 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 132 Airbus Model A320 series airplanes of
U.S. registry will be affected by this AD, that it will take
approximately 8 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 inspection required by this AD
on U.S. operators is estimated to be $63,360, or $480 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
[[Page 49273]]
that no operator would accomplish those actions in the future if this
AD were not adopted.
Should an operator elect to accomplish the modification, it would
take approximately 5 work hours per airplane to accomplish the actions,
at an average labor rate of $60 per work hour. Based on these figures,
the cost impact of the optional modification provided by this AD on
U.S. operators is estimated to be $300 per airplane.
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, 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:
98-18-24 Airbus Industrie: Amendment 39-10740. Docket 97-NM-156-AD.
Applicability: Model A320 series airplanes on which Airbus
Modification 21778 (reference Airbus Service Bulletin A320-53-1072,
dated November 7, 1995, as revised by Change Notice 0A, dated July
5, 1996) 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 (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 correct fatigue cracking in the inner flange of door frame
66, left and right, which could result in reduced structural
integrity of the airplane, accomplish the following:
(a) Prior to the accumulation of 20,000 total flight cycles, or
within 1 year after the effective date of this AD, whichever occurs
later: Perform a rotating probe eddy current inspection to detect
cracking around the edges of the gusset plate attachment holes of
the inner flange of door frame 66, left and right, at stringer
positions P18, P20, P22, P18, P20, and P22, in accordance with
Airbus Service Bulletin A320-53-1071, dated November 7, 1995, as
revised by Change Notice 0A, dated July 5, 1996. If any crack is
detected, prior to further flight, repair in accordance with a
method approved by the Manager, International Branch, ANM-116, FAA,
Transport Airplane Directorate. Repeat the inspection thereafter at
intervals not to exceed 20,000 flight cycles.
(b) Modification of the gusset plate attachment holes of the
inner flange of door frame 66, left and right (Airbus Modification
21778), in accordance with Airbus Service Bulletin A320-53-1072,
dated November 7, 1995, as revised by Change Notice 0A, dated July
5, 1996, constitutes terminating action for the repetitive
inspection requirements of this AD.
(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.
(d) Special flight permits may be issued in accordance with
Secs. 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 inspections shall be done in accordance with Airbus
Service Bulletin A320-53-1071, dated November 7, 1995, as revised by
Change Notice 0A, dated July 5, 1996. 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 96-234-087(B), dated October 20, 1996.
(f) This amendment becomes effective on October 20, 1998.
Issued in Renton, Washington, on August 28, 1998.
Vi L. Lipski,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-24248 Filed 9-14-98; 8:45 am]
BILLING CODE 4910-13-U
