[Federal Register Volume 62, Number 202 (Monday, October 20, 1997)]
[Rules and Regulations]
[Pages 54372-54373]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-27354]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 96-NM-126-AD; Amendment 39-10165; AD 97-21-12]
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
a one-time inspection to detect fatigue cracking in the area of the
center wing-to-fuselage attachment fitting, and repair, if necessary.
This amendment also would require installation of a reinforcing plate
in the attachment area of that fitting. This amendment is prompted by a
report from the manufacturer indicating that, during full-scale fatigue
testing, fatigue cracks were detected in this area. The actions
specified by this AD are intended to prevent fatigue cracking, which
consequently could reduce the structural integrity of this area.
DATES: Effective November 24, 1997.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of November 24, 1997.
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: Greg Dunn, Aerospace Engineer,
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2799; 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 3, 1997 (62 FR
9388). That action proposed to require a one-time inspection to detect
fatigue cracking in the area where the center wing-to-fuselage
attachment fitting is located, and repair, if necessary. In addition,
that action proposed the installation of a reinforcing plate in the
attachment area of the center wing-to-fuselage attachment fitting,
after inspection and any necessary repairs have been accomplished.
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.
Conclusion
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 2 CASA Model CN-235 series airplanes of U.S.
registry will be affected by this AD.
It will take approximately 25 work hours per airplane to accomplish
the required actions, at an average labor rate of $60 per work hour.
Required parts will cost approximately $645 per airplane. Based on
these figures, the cost impact of the AD on U.S. operators is estimated
to be $4,290, or $2,145 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 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:
97-21-12 Construcciones Aeronauticas, S.A. CASA: Amendment 39-
10165.Docket 96-NM-126-AD.
Applicability: Model CN-235 series airplanes, as listed in CASA
Service Bulletin SB-235-53-20, Revision 2, dated June 9, 1994 (for
non-military airplanes); and Service Bulletin SB-235-53-20M,
Revision 1, dated November 27, 1995 (for military 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
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.
[[Page 54373]]
To prevent fatigue cracking in the area of the center wing-to-
fuselage attachment fitting, which consequently could reduce the
structural integrity of this area, accomplish the following:
(a) For non-military airplanes: Prior to the accumulation of
17,000 total landings, accomplish the actions specified in
paragraphs (a)(1), (a)(2), and (a)(3) of this AD:
(1) Remove all parts and other items in the area of the center
wing-to-fuselage attachment fitting, in accordance with Paragraph
2.B. (``Removal'') of the Accomplishment Instructions of CASA
Service Bulletin SB-235-53-20, Revision 2, dated June 9, 1994.
(2) After all parts and other items have been removed in
accordance with paragraph (a)(1) of this AD, conduct a visual
inspection, using a magnifier of at least 10x magnitude, to detect
fatigue cracking in this area (ref: Figure 1, Sheet 1, of the
service bulletin). If any cracking is detected, prior to further
flight and prior to installing the reinforcing plate in accordance
with paragraph (a)(3) of this AD, repair in a manner approved by the
Manager, Standardization Branch, ANM-113, FAA, Transport Airplane
Directorate.
(3) Install a reinforcing plate having CASA part number (P/N)
35-25010-0101 in the attachment area of the center wing-to-fuselage
attachment fitting, in accordance with the service bulletin.
(b) For military airplanes: Prior to the accumulation of 15,000
total landings, accomplish the actions specified in paragraphs
(b)(1), (b)(2), and (b)(3) of this AD:
(1) Remove all parts and other items in the area of the center
wing-to-fuselage attachment fitting, in accordance with Paragraph
2.B. (``Removal'') of the Accomplishment Instructions of CASA
Service Bulletin SB-235-53-20M, Revision 1, dated November 27, 1995.
(2) After all parts and other items have been removed in
accordance with paragraph (b)(1) of this AD, conduct a visual
inspection, using a magnifier of at least 10x magnitude, to detect
fatigue cracking in this area (ref: Figure 1, Sheet 1, of the
service bulletin). If any cracking is detected, prior to further
flight and prior to installing the reinforcing plate in accordance
with paragraph (b)(3) of this AD, repair in a manner approved by the
Manager, Standardization Branch, ANM-113, FAA.
(3) Install a reinforcing plate having CASA part number (P/N)
35-25010-0101 in the attachment area of the center wing-to-fuselage
attachment fitting, in accordance with the 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, Standardization Branch, ANM-113.
Operators shall submit their requests through an appropriate FAA
Principal Maintenance Inspector, who may add comments and then send
it to the Manager, Standardization Branch, ANM-113.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Standardization Branch, ANM-113.
(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) Certain actions shall be done in accordance with CASA
Service Bulletin SB-235-53-20M, Revision 1, dated November 27, 1995
(for military airplanes); and CASA Service Bulletin SB-235-53-20,
Revision 2, dated June 9, 1994 (for non-military airplanes), which
contains the following list of effective pages:
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Revision level
Page No. shown on page Date shown on page
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1............................. 1................ April 13, 1994.
2............................. 2................ June 9, 1994.
3-11.......................... Original......... July 29, 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 03/94, dated August 1994.
(f) This amendment becomes effective on November 24, 1997.
Issued in Renton, Washington, on October 9, 1997.
James V. Devany,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 97-27354 Filed 10-17-97; 8:45 am]
BILLING CODE 4910-13-U
