[Federal Register Volume 63, Number 106 (Wednesday, June 3, 1998)]
[Rules and Regulations]
[Pages 30112-30114]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-14213]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-NM-43-AD; Amendment 39-10548; AD 98-11-23]
RIN 2120-AA64
Airworthiness Directives; Construcciones Aeronauticas, S.A.
(CASA) Model CN-235 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 CASA Model CN-235 series airplanes, that requires
modification of certain fastener holes of the center wing. 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 prevent fatigue cracking in this
area, which could result in reduced structural integrity of the wing.
DATES: Effective July 8, 1998.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of July 8, 1998.
ADDRESSES: The service information referenced in this AD may be
obtained from Construcciones Aeronauticas, S.A., Getafe, Madrid, Spain.
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
[[Page 30113]]
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 CASA Model CN-235 series
airplanes was published in the Federal Register on March 23, 1998 (63
FR 13801). That action proposed to require modification of certain
fastener holes of the center wing.
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.
Explanation of Changes Made to This Final Rule
In the proposal, the FAA inadvertently omitted reference to Annex
1, dated June 10, 1993, of CASA Service Bulletin SB-235-57-05, Revision
2, dated June 21, 1996. Therefore, the FAA has revised the final rule
accordingly.
Conclusion
The FAA has determined that air safety and the public interest
require the adoption of the rule with the change previously described.
The FAA has determined that this change will neither increase the
economic burden on any operator nor increase the scope of the AD.
Cost Impact
The FAA estimates that 2 airplanes of U.S. registry will be
affected by this AD.
The FAA estimates that the actions specified in CASA Service
Bulletin SB-235-57-14, will be required to be accomplished on one
airplane of U.S. registry. These required actions will take
approximately 220 work hours per airplane to accomplish, at an average
labor rate of $60 per work hour. Required parts will cost approximately
$719 per airplane. Based on these figures, the cost impact of the
inspection required by this AD on the single U.S. operator is estimated
to be $13,919.
For CASA Model CN-235 series airplane, serial number C-011, on
which the actions specified in CASA Service Bulletin SB-235-57-05 will
be required to be accomplished, those required actions will take
approximately 1,900 work hours per airplane to accomplish, at an
average labor rate of $60 per work hour. Required parts will cost
approximately $11,330 per airplane. Based on these figures, the cost
impact of the required actions for that airplane is estimated to be
$125,330.
The cost impact figures discussed above are 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, 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:
98-11-23 Construcciones Aeronauticas S.A. (CASA): Amendment 39-
10548. Docket 97-NM-43-AD.
Applicability: Model CN-235 series airplanes; as listed in CASA
Service Bulletins SB-235-57-14, Revision 1, dated June 21, 1996; and
SB-235-57-05, Revision 2, dated June 21, 1996, including Annex 1,
dated June 10, 1993; and Model CN-235 having serial number C-011;
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 (d) 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 fatigue cracking in the fastener holes of the center
wing, which could result in reduced structural integrity of the
wing, accomplish the following:
(a) For airplanes listed in CASA Service Bulletins SB-235-57-14,
Revision 1, dated June 21, 1996; and SB-235-57-05, Revision 2, dated
June 21, 1996, including Annex 1, dated June 10, 1993: Perform a
rototest inspection of the fastener holes of the center wing to
detect cracking, in accordance with the applicable service bulletin,
at the time specified in paragraph (c) of this AD.
(1) If no crack is found, prior to further flight, cold work the
fastener holes in accordance with the applicable service bulletin.
(2) If any crack is found, prior to further flight, remove it in
accordance with the service bulletin; repeat the rototest inspection
to detect cracking; and cold work the fastener holes, in accordance
with the applicable service bulletin. If any crack is found that
cannot be removed using the procedures specified in the applicable
service bulletin, prior to further flight, repair it in accordance
with a method approved by the Manager, International Branch, ANM-
116, FAA, Transport Airplane Directorate.
(b) For airplane serial number C-011: Perform a rototest
inspection of the fastener holes of the center wing to detect
cracking, in accordance with CASA Service Bulletin SB-235-57-05,
Revision 2, dated June 21, 1996, including Annex 1, dated June 10,
1993, at the time specified in paragraph (c) of this AD.
(1) If no crack is found, prior to further flight, cold work the
fastener holes in accordance with the service bulletin.
(2) If any crack is found, prior to further flight, remove it in
accordance with the service bulletin; repeat the rototest inspection
to detect cracking; and cold work the fastener holes, in accordance
with the service bulletin. If any crack is found that cannot be
removed using the procedures specified in the service bulletin,
prior to further flight, repair it in accordance with a method
approved by the Manager, International Branch, ANM-116.
(c) Accomplish the inspection required by paragraph (a) or (b)
of this AD, as applicable,
[[Page 30114]]
at the later of the times specified in paragraphs (c)(1) and (c)(2)
of this AD.
(1) Prior to the accumulation of 17,000 total flight cycles or
37,400 total flight hours, whichever occurs first.
(2) Within 6 months after the effective date of this AD.
(d) 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.
(e) 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.
(f) The actions shall be done in accordance with CASA Service
Bulletin SB-235-57-14, Revision 1, dated June 21, 1996, and CASA
Service Bulletin SB-235-57-05, Revision 2, dated June 21, 1996,
including Annex 1, dated June 10, 1993, which contains the following
list of effective pages:
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Revision
level
Page Nos. shown on Date shown on page
page
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1, 3-5, 12, 26-29, 33, 34, 45-52.. 2 June 21, 1996.
2, 6-11, 13-25, 30-32, 35-44, 53- 1 March 13, 1995.
65.
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Annex 1
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1-46.............................. 5 June 10, 1993.
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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 Construcciones Aeronauticas,
S.A., Getafe, Madrid, Spain. 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 Spanish
airworthiness directive 04/94, dated August 1994.
(g) This amendment becomes effective on July 8, 1998.
Issued in Renton, Washington, on May 22, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-14213 Filed 6-2-98; 8:45 am]
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