[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:

------------------------------------------------------------------------
                                  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]
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