[Federal Register Volume 63, Number 183 (Tuesday, September 22, 1998)]
[Rules and Regulations]
[Pages 50506-50508]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-25149]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-NM-20-AD; Amendment 39-10792; AD 98-20-26]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A320-111, -211, and -231
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 A320-111, -211, and -231 series
airplanes, that requires repetitive inspections to detect missing or
cracked bolts and fittings of the frame-to-pressure-floor connection;
and corrective actions, if necessary. This amendment also provides for
optional terminating action for the repetitive inspections of the
affected fittings. 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 in the bolts and fittings of the frame-to-
pressure-floor connection, which could result in reduced structural
integrity of the airplane.
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
[[Page 50507]]
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 A320-111, -
211, and -231 series airplanes was published in the Federal Register on
April 14, 1998 (63 FR 18153). That action proposed to require
repetitive inspections to detect missing or cracked bolts and fittings
of the frame-to-pressure-floor connection; and corrective actions, if
necessary. That action also proposed to provide for optional
terminating action for the repetitive inspections of the affected
fittings.
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 proposed rule.
Request To Allow Flight With Known Cracks
One commenter requests that the FAA allow flight of the airplane
with known cracks. The commenter states that the structure of Airbus
Model A320 series airplanes is classified as damage tolerant. The
commenter also states that it has defined a certain number of flights
that allows continued operation with a cracked or broken part,
depending on the measured crack length and number of cracked bolts
detected.
The FAA does not concur with the commenter's request to allow
flight of an airplane with known cracks. It is the FAA's policy to
require repair of known cracks prior to further flight, except in
certain cases of unusual need (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's 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.
Additionally, the FAA's policy applies to airplanes certificated to
damage tolerance evaluation regulations as well as those not so
certificated. The FAA finds that 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'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, among other things, such
circumstances as legitimate difficulty in acquiring parts to accomplish
repairs. Under such conditions, the FAA may allow temporary deferral of
the repair, subject to a stringent inspection program acceptable to the
FAA. However, since the FAA is not aware of any unusual need for repair
deferral in regard to this AD, the FAA finds that the compliance times
specified in the final rule are adequate to allow operators to acquire
parts to have on hand in the event that a crack is detected during an
inspection. Therefore, the FAA has determined that, due to safety
implications and consequences associated with such cracking, any
subject bolt or fitting that is found to be cracked or broken must be
repaired or modified prior to further flight. No change to the final
rule is necessary.
Request To Reference Earlier Airbus Service Bulletins as
Terminating Action
One commenter requests that the proposed AD be revised to reference
Airbus Service Bulletin A320-53-1015, dated December 12, 1995, and
Revision 1, dated July 25, 1995, as additional sources of service
information for accomplishment of the optional terminating action. The
FAA concurs. The FAA finds that the procedures specified in the earlier
revisions of the subject service bulletin are essentially identical to
those specified in Revision 02 of the service bulletin (which was
referenced in the NPRM as the appropriate source of service information
for accomplishment of the optional terminating action). Therefore, the
FAA has revised the final rule to include a new NOTE to specify that
reinforcement of the fitting prior to the effective date of this AD, in
accordance with the earlier revisions of the subject service bulletin,
is considered acceptable for compliance with the reinforcement
specified in paragraphs (a)(2) and (b) of this AD.
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 with the changes described
previously. The FAA has determined that these changes will neither
increase the economic burden on any operator nor increase the scope of
the AD.
Cost Impact
The FAA estimates that 5 Model A320-111, -211, and -231 series
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
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 $2,700, or $540 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.
Should an operator elect to accomplish the optional terminating
action that is provided by this AD action, it would take approximately
119 work hours to accomplish it, at an average labor rate of $60 per
work hour. The cost of required parts would be approximately $12,920
per airplane. Based on these figures, the cost impact of the optional
terminating action would be $20,060 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
[[Page 50508]]
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:
98-20-26 Airbus Industrie: Amendment 39-10792. Docket 98-NM-20-AD.
Applicability: Model A320-111, -211, and -231 series airplanes;
as listed in Airbus Service Bulletin A320-53-1083, Revision 2, dated
August 28, 1997; 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 fatigue cracking in the bolts and fittings
of the frame-to-pressure-floor connection, 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 60 days after the effective date of this AD, whichever occurs
later, perform a detailed visual inspection to detect cracked or
missing bolts and fittings of the frame-to-pressure-floor connection
at frames 43 and 44, in accordance with Airbus Service Bulletin
A320-53-1083, Revision 2, dated August 28, 1997. If no crack is
detected, repeat the detailed visual inspection thereafter at
intervals not to exceed 5,100 flight cycles.
(1) If any bolt is found to be cracked or missing during any
inspection required by paragraph (a) of this AD, prior to further
flight, replace the bolt with a new bolt in accordance with the
service bulletin. Repeat the detailed visual inspection thereafter
at intervals not to exceed 5,100 flight cycles.
(2) If any fitting is found to be cracked during any inspection
required by paragraph (a) of this AD, prior to further flight,
accomplish the actions specified in paragraph (b) of this AD for the
cracked fitting and its corresponding bolts and fuselage frame, in
accordance with Airbus Service Bulletin A320-53-1015, Revision 02,
dated July 17, 1997.
(b) Reinforcement of the fitting in accordance with Airbus
Service Bulletin A320-53-1015, Revision 02, dated July 17, 1997,
constitutes terminating action for the requirements of this AD for
the affected fitting.
Note 2: Reinforcement of the fitting accomplished prior to the
effective date of this AD in accordance with Airbus Service Bulletin
A320-53-1015, dated December 12, 1995, or Revision 1, dated July 25,
1995, is considered acceptable for compliance with the reinforcement
specified in paragraphs (a)(2) and (b) 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, 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 3: 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 inspections shall be done in accordance with Airbus
Service Bulletin A320-53-1083, Revision 2, dated August 28, 1997.
The reinforcement, if accomplished, shall be done in accordance with
Airbus Service Bulletin A320-53-1015, Revision 02, dated July 17,
1997. 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 4: The subject of this AD is addressed in French
airworthiness directive 97-316-110(B), dated October 22, 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. 98-25149 Filed 9-21-98; 8:45 am]
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