Airworthiness Directives; Construcciones Aeronauticas, S.A. (CASA), Model CN-235, CN-235-100, CN-235-200, and CN-235-300 Airplanes, 69247-69249 [E9-30707]

Download as PDF Federal Register / Vol. 74, No. 250 / Thursday, December 31, 2009 / Rules and Regulations 69247 11 For children, cheese may be substituted for milk at the rate of 1 pound of cheese per 3 quarts of milk. No more than 1 lb. of cheese may be substituted for milk. With medical documentation, additional amounts of cheese may be substituted in cases of lactose intolerance or other qualifying conditions, up to the maximum allowance for fluid milk. 12 For children, soy-based beverage and tofu may be substituted for milk only with medical documentation for qualifying conditions. Soy-based beverage may be substituted for milk, with medical documentation, for children in Food Package IV on a quart for quart basis up to the total maximum allowance of milk. Tofu may be substituted for milk, with medical documentation, for children in Food Package IV at the rate of 1 pound of tofu per 1 quart of milk up to the total maximum allowance of milk. 13 For women, cheese or calcium-set tofu may be substituted for milk at the rate of 1 pound of cheese per 3 quarts of milk or 1 pound of tofu per 1 quart of milk. A maximum of 4 quarts of milk can be substituted in this manner in Food Packages V and VI; however, no more than 1 pound of cheese may be substituted for milk. A maximum of 6 quarts of milk can be substituted in this manner in Food Package VII; therefore, no more than 2 lbs. of cheese may be substituted for milk. With medical documentation, additional amounts of cheese or tofu may be substituted, up to the maximum allowances for fluid milk, in cases of lactose intolerance or other qualifying conditions. 14 For women, soy-based beverage may be substituted for milk at the rate of 1 quart of soy-based beverage for 1 quart of milk up to the total maximum monthly allowance of milk. 15 32 dry ounces of infant cereal may be substituted for 36 ounces of breakfast cereal. 16 At least one half of the total number of breakfast cereals on the State agency’s authorized food list must have whole grain as the primary ingredient and meet labeling requirements for making a health claim as a ‘‘whole grain food with moderate fat content’’ as defined in Table 4 of paragraph (e)(12) of this section. 17 Processed (canned, frozen, dried) fruits and vegetables may be substituted for fresh fruits and vegetables. Dried fruit and dried vegetables are not authorized for children. 18 The monthly value of the fruit/vegetable cash-value vouchers will be adjusted annually for inflation as described in § 246.16(j). 19 Brown rice, bulgur (cracked wheat), oatmeal, whole-grain barley, soft corn or whole wheat tortillas may be substituted for whole wheat bread on an equal weight basis. 20 Canned legumes may be substituted for dried legumes at the rate of 64 oz of canned beans for 1 lb dried beans. Issuance of two additional combinations of dry or canned beans/peas is authorized for the Pregnant and Partially Breastfeeding (up to 1 year postpartum) category and Fully Breastfeeding (Enhanced) (up to 1 year postpartum) category: 1 lb. Dry and 64 oz. Canned beans/peas (and no peanut butter); or 2 lb. Dry or 128 oz. Canned beans/peas (and no peanut butter) or 36 oz. peanut butter (and no beans). * * § 246.16 * * * [Amended] 3. Paragraph 246.16(j) (2) (ii) is amended by revising ‘‘$8’’ to read ‘‘$10’’ ■ Dated: December 24, 2009. Julia Paradis, Administrator, Food and Nutrition Service. [FR Doc. E9–30991 Filed 12–30–09; 8:45 am] BILLING CODE 3410–30–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2009–0637; Directorate Identifier 2008–NM–183–AD; Amendment 39–16153; AD 2009–26–14] RIN 2120–AA64 Airworthiness Directives; Construcciones Aeronauticas, S.A. (CASA), Model CN–235, CN–235–100, CN–235–200, and CN–235–300 Airplanes erowe on DSK5CLS3C1PROD with RULES AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. SUMMARY: We are superseding an existing airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: VerDate Nov<24>2008 13:48 Dec 30, 2009 Jkt 220001 * * * As a consequence of cracks [that were originally] detected on some CN–235 aircraft, in flap fittings P/N 35–15501–0101, –0102, –0201 and –0202, attaching the structure of the outer flaps to their rear supports and, in the adjacent structure, DGAC Spain issued AD Nr. 01/97[.] * * * Since AD 1/97 Rev.1 was published, similar cracks have been detected in flaps longerons. * * * * * * * * Fatigue cracking of the rear internal support fittings and longerons of the outer flap structure could result in failure of the outer flaps, and consequent reduced controllability of the airplane. We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective February 4, 2010. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of February 4, 2010. ADDRESSES: You may examine the AD docket on the Internet at https:// www.regulations.gov or in person at the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC. FOR FURTHER INFORMATION CONTACT: Shahram Daneshmandi, Aerospace Engineer, International Branch, ANM– 116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1112; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on July 15, 2009 (74 FR 34272). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: As a consequence of cracks [that were originally] detected on some CN–235 aircraft, in flap fittings P/N 35–15501–0101, –0102, –0201 and –0202, attaching the structure of the outer flaps to their rear supports and, in ´ the adjacent structure, DGAC [Direccion ´ General de Aviacion Civil] Spain issued AD Nr. 01/97 which required, pending the analysis of the problem, boroscopic inspections of the attachment zones between both outer flaps to their rear support. After concluding that process and based on the investigation results, DGAC Spain issued AD Nr. 1/97 Rev.1 [which corresponds to FAA AD 99–07–13] to require the replacement of the outer flaps with new designed parts, as specified in EADS–CASA Service Bulletin (SB) 235–57–20. Since AD 1/97 Rev.1 was published, similar cracks have been detected in flaps longerons. EADS–CASA issued SB 235–57– 20 Revision 1, extending the scope of the inspection to these flaps longerons, instructing the drilling of holes to facilitate the inspection and introducing an improved outer flap replacement kit that included a new improved longeron. SB 235–57–20 Revision 2 has been issued to add useful references and to update the applicability. For the reasons described above, this new EASA [European Aviation Safety Agency] AD retains the requirements of DGAC Spain AD Nr. 1/97 Rev.1, which is superseded, and confirms the approval of additional outer flaps replacement options, as specified in paragraph 2 E.2 of EADS–CASA SB 235–57– 20 R2. Fatigue cracking of the rear internal support fittings and longerons of the outer flap structure could result in failure of the outer flaps, and E:\FR\FM\31DER1.SGM 31DER1 69248 Federal Register / Vol. 74, No. 250 / Thursday, December 31, 2009 / Rules and Regulations consequent reduced controllability of the airplane. You may obtain further information by examining the MCAI in the AD docket. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM or on the determination of the cost to the public. Conclusion We reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed. Differences Between This AD and the MCAI or Service Information We have reviewed the MCAI and related service information and, in general, agree with their substance. But we might have found it necessary to use different words from those in the MCAI to ensure the AD is clear for U.S. operators and is enforceable. In making these changes, we do not intend to differ substantively from the information provided in the MCAI and related service information. We might also have required different actions in this AD from those in the MCAI in order to follow our FAA policies. Any such differences are highlighted in a NOTE within the AD. Costs of Compliance We estimate that this AD will affect 8 products of U.S. registry. We also estimate that it will take about 69 workhours per product to comply with the basic requirements of this AD. The average labor rate is $80 per work-hour. Required parts will cost about $193,603 per product. Where the service information lists required parts costs that are covered under warranty, we have assumed that there will be no charge for these parts. As we do not control warranty coverage for affected parties, some parties may incur costs higher than estimated here. Based on these figures, we estimate the cost of this AD to the U.S. operators to be $1,592,984, or $199,123 per product. erowe on DSK5CLS3C1PROD with RULES Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ‘‘Subtitle VII: Aviation Programs,’’ describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in ‘‘Subtitle VII, Part A, Subpart III, Section 44701: VerDate Nov<24>2008 13:48 Dec 30, 2009 Jkt 220001 General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect 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. For the reasons discussed above, I certify this AD: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the 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. We prepared a regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD docket. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains the NPRM, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: ■ PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Amendment 39–11098 (64 FR 15659, April 1, 1999) and adding the following new AD: ■ 2009–26–14 CONSTRUCCIONES AERONAUTICAS, S.A. (CASA): Amendment 39–16153. Docket No. FAA–2009–0637; Directorate Identifier 2008–NM–183–AD. Effective Date (a) This airworthiness directive (AD) becomes effective February 4, 2010. Affected ADs (b) This AD supersedes AD 99–07–13, Amendment 39–11098. Applicability (c) This AD applies to CASA Model CN– 235, CN–235–100, CN–235–200, and CN–235–300 airplanes, certificated in any category, all serial numbers, if part number (P/N) 35–15501–0001, –0002, –0003, or –0004, or P/N 35–A0736–0001 or –0002 outer flaps are installed. Subject (d) Air Transport Association (ATA) of America Code 57: Wings. Reason (e) The mandatory continuing airworthiness information (MCAI) states: As a consequence of cracks [that were originally] detected on some CN–235 aircraft, in flap fittings P/N 35–15501–0101, –0102, –0201 and –0202, attaching the structure of the outer flaps to their rear supports and, in the adjacent structure, DGAC Spain issued AD Nr. 01/97 which required, pending the analysis of the problem, boroscopic inspections of the attachment zones between both outer flaps to their rear support. After concluding that process and based on the ´ investigation results, DGAC [Direccion ´ General de Aviacion Civil] Spain issued AD Nr. 1/97 Rev.1 [which corresponds to FAA AD 99–07–13] to require the replacement of the outer flaps with new designed parts, as specified in EADS–CASA Service Bulletin (SB) 235–57–20. Since AD 1/97 Rev.1 was published, similar cracks have been detected in flaps longerons. EADS–CASA issued SB 235–57– 20 Revision 1, extending the scope of the inspection to these flaps longerons, instructing the drilling of holes to facilitate the inspection and introducing an improved outer flap replacement kit that included a new improved longeron. SB 235–57–20 Revision 2 has been issued to add useful references and to update the applicability. For the reasons described above, this new EASA [European Aviation Safety Agency] AD retains the requirements of DGAC Spain AD Nr. 1/97 Rev.1, which is superseded, and confirms the approval of additional outer flaps replacement options, as specified in paragraph 2 E.2 of EADS–CASA SB 235–57– 20 R2. Fatigue cracking of the rear internal support fittings and longerons of the outer flap E:\FR\FM\31DER1.SGM 31DER1 Federal Register / Vol. 74, No. 250 / Thursday, December 31, 2009 / Rules and Regulations erowe on DSK5CLS3C1PROD with RULES structure could result in failure of the outer flaps, and consequent reduced controllability of the airplane. Actions and Compliance (f) Unless already done, do the following actions. (1) For airplanes equipped with P/N 35–A0736–0001 or –0002 outer flaps: Within 300 flight cycles after the effective date of this AD, do a borescopic inspection to detect cracking of the outer flaps fittings and longerons, in accordance with the Accomplishment Instructions of EADS– CASA Service Bulletin SB–235–57–20, Revision 2, dated March 30, 2007. (2) For airplanes equipped with P/N 35– 15501–0001, –0002, –0003, or –0004 outer flaps: At the earlier of the times specified in paragraphs (f)(2)(i) and (f)(2)(ii) of this AD, do a borescopic inspection to detect cracking of the outer flaps fittings; and within 300 flight cycles after the effective date of this AD, do a borescopic inspection to detect cracking of the longerons. Do the inspections in accordance with the Accomplishment Instructions of EADS–CASA Service Bulletin SB–235–57–20, Revision 2, dated March 30, 2007. (i) Within 600 flight cycles after the most recent inspection done in accordance with AD 99–07–13, or within 14 days after the effective date of this AD, whichever occurs later. (ii) Within 300 flight cycles after the effective date of this AD. (3) If, during any inspection required by paragraph (f)(1) or (f)(2) of this AD, no crack is detected, repeat the borescopic inspections of the outer flap fittings and longerons in accordance with the Accomplishment Instructions of EADS–CASA Service Bulletin SB–235–57–20, Revision 2, dated March 30, 2007, thereafter at intervals not to exceed 300 flight cycles or 6 months, whichever occurs first, until the replacement specified in paragraph (f)(4) or (f)(5) of this AD is accomplished. (4) If any crack is detected during any inspection required by paragraph (f)(1), (f)(2), or (f)(3) of this AD, prior to further flight, replace the outer flap with a new or retrofitted flap in accordance with the Accomplishment Instructions of EADS– CASA Service Bulletin SB–235–57–20, Revision 2, dated March 30, 2007. Such replacement constitutes terminating action for the repetitive borescopic inspection required by this AD for the replaced outer flap only. (5) For affected parts that have not been replaced in accordance with paragraph (f)(4) of this AD: At the later of the times specified in paragraphs (f)(5)(i) and (f)(5)(ii) of this AD, replace each outer flap with a new or retrofitted outer flap in accordance with the Accomplishment Instructions of EADS– CASA Service Bulletin SB–235–57–20, Revision 2, dated March 30, 2007. Replacing all outer flaps terminates the requirements of this AD. (i) Before the accumulation of 4,000 total flight cycles on the flap. (ii) Within 1,200 flight cycles or 24 months after the effective date of this AD, whichever occurs first. VerDate Nov<24>2008 13:48 Dec 30, 2009 Jkt 220001 (6) Actions done before the effective date of this AD in accordance with CASA Service Bulletin SB–235–57–20, dated December 23, 1997; or EADS–CASA Service Bulletin SB–235–57–20, Revision 1, dated April 30, 2004; are acceptable for compliance with the corresponding requirements of paragraph (f)(2) of this AD. FAA AD Differences Note 1: This AD differs from the MCAI and/or service information as follows: No differences. Other FAA AD Provisions (g) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Shahram Daneshmandi, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057– 3356; telephone (425) 227–1112; fax (425) 227–1149. Before using any approved AMOC on any airplane to which the AMOC applies, notify your principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a principal inspector, your local Flight Standards District Office. The AMOC approval letter must specifically reference this AD. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120–0056. Related Information (h) Refer to MCAI EASA Airworthiness Directive 2008–0119, dated June 27, 2008; and EADS–CASA Service Bulletin SB–235– 57–20, Revision 2, dated March 30, 2007; for related information. Material Incorporated by Reference (i) You must use EADS–CASA Service Bulletin SB–235–57–20, Revision 2, dated March 30, 2007, to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact EADS–CASA, Military Transport Aircraft Division (MTAD), Integrated Customer Services (ICS), ´ Technical Services, Avenida de Aragon 404, PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 69249 28022 Madrid, Spain; telephone +34 91 585 55 84; fax +34 91 585 55 05; e-mail MTA.TechnicalService@casa.eads.net; Internet https://www.eads.net. (3) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227–1221 or 425–227–1152. (4) You may also review copies of the service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https://www.archives.gov/federal_register/ code_of_federal_regulations/ibr_ locations.html. Issued in Renton, Washington, on December 16, 2009. Stephen P. Boyd, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9–30707 Filed 12–30–09; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2009–0686; Directorate Identifier 2009–NM–044–AD; Amendment 39–16155; AD 2009–26–16] RIN 2120–AA64 Airworthiness Directives; McDonnell Douglas Corporation Model MD–11 and MD–11F Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. SUMMARY: We are adopting a new airworthiness directive (AD) for certain Model MD–11 and MD–11F airplanes. This AD requires a one-time inspection to determine if wires touch the upper surface of the center upper auxiliary fuel tank and marking the location, if necessary; a one-time inspection of all wire bundles above the center upper auxiliary fuel tank for splices and damage; a one-time inspection for damage to the fuel vapor barrier seal and upper surface of the center upper auxiliary fuel tank; and corrective actions, if necessary. This AD also requires installation of nonmetallic barrier/shield sleeving, new clamps, new attaching hardware, and a new extruded channel. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to reduce the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result E:\FR\FM\31DER1.SGM 31DER1

Agencies

[Federal Register Volume 74, Number 250 (Thursday, December 31, 2009)]
[Rules and Regulations]
[Pages 69247-69249]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-30707]


=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0637; Directorate Identifier 2008-NM-183-AD; 
Amendment 39-16153; AD 2009-26-14]
RIN 2120-AA64


Airworthiness Directives; Construcciones Aeronauticas, S.A. 
(CASA), Model CN-235, CN-235-100, CN-235-200, and CN-235-300 Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: We are superseding an existing airworthiness directive (AD) 
for the products listed above. This AD results from mandatory 
continuing airworthiness information (MCAI) originated by an aviation 
authority of another country to identify and correct an unsafe 
condition on an aviation product. The MCAI describes the unsafe 
condition as:

    * * * As a consequence of cracks [that were originally] detected 
on some CN-235 aircraft, in flap fittings P/N 35-15501-0101, -0102, 
-0201 and -0202, attaching the structure of the outer flaps to their 
rear supports and, in the adjacent structure, DGAC Spain issued AD 
Nr. 01/97[.] * * *
    Since AD 1/97 Rev.1 was published, similar cracks have been 
detected in flaps longerons. * * *
* * * * *

Fatigue cracking of the rear internal support fittings and longerons of 
the outer flap structure could result in failure of the outer flaps, 
and consequent reduced controllability of the airplane. We are issuing 
this AD to require actions to correct the unsafe condition on these 
products.

DATES: This AD becomes effective February 4, 2010.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of February 4, 
2010.

ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov or in person at the U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC.

FOR FURTHER INFORMATION CONTACT: Shahram Daneshmandi, Aerospace 
Engineer, International Branch, ANM-116, Transport Airplane 
Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; 
telephone (425) 227-1112; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an AD that would apply to the specified products. 
That NPRM was published in the Federal Register on July 15, 2009 (74 FR 
34272). That NPRM proposed to correct an unsafe condition for the 
specified products. The MCAI states:

    As a consequence of cracks [that were originally] detected on 
some CN-235 aircraft, in flap fittings P/N 35-15501-0101, -0102, -
0201 and -0202, attaching the structure of the outer flaps to their 
rear supports and, in the adjacent structure, DGAC [Direcci[oacute]n 
General de Aviaci[oacute]n Civil] Spain issued AD Nr. 01/97 which 
required, pending the analysis of the problem, boroscopic 
inspections of the attachment zones between both outer flaps to 
their rear support. After concluding that process and based on the 
investigation results, DGAC Spain issued AD Nr. 1/97 Rev.1 [which 
corresponds to FAA AD 99-07-13] to require the replacement of the 
outer flaps with new designed parts, as specified in EADS-CASA 
Service Bulletin (SB) 235-57-20.
    Since AD 1/97 Rev.1 was published, similar cracks have been 
detected in flaps longerons. EADS-CASA issued SB 235-57-20 Revision 
1, extending the scope of the inspection to these flaps longerons, 
instructing the drilling of holes to facilitate the inspection and 
introducing an improved outer flap replacement kit that included a 
new improved longeron. SB 235-57-20 Revision 2 has been issued to 
add useful references and to update the applicability.
    For the reasons described above, this new EASA [European 
Aviation Safety Agency] AD retains the requirements of DGAC Spain AD 
Nr. 1/97 Rev.1, which is superseded, and confirms the approval of 
additional outer flaps replacement options, as specified in 
paragraph 2 E.2 of EADS-CASA SB 235-57-20 R2.

Fatigue cracking of the rear internal support fittings and longerons of 
the outer flap structure could result in failure of the outer flaps, 
and

[[Page 69248]]

consequent reduced controllability of the airplane. You may obtain 
further information by examining the MCAI in the AD docket.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM or on the determination of 
the cost to the public.

Conclusion

    We reviewed the available data and determined that air safety and 
the public interest require adopting the AD as proposed.

Differences Between This AD and the MCAI or Service Information

    We have reviewed the MCAI and related service information and, in 
general, agree with their substance. But we might have found it 
necessary to use different words from those in the MCAI to ensure the 
AD is clear for U.S. operators and is enforceable. In making these 
changes, we do not intend to differ substantively from the information 
provided in the MCAI and related service information.
    We might also have required different actions in this AD from those 
in the MCAI in order to follow our FAA policies. Any such differences 
are highlighted in a NOTE within the AD.

Costs of Compliance

    We estimate that this AD will affect 8 products of U.S. registry. 
We also estimate that it will take about 69 work-hours per product to 
comply with the basic requirements of this AD. The average labor rate 
is $80 per work-hour. Required parts will cost about $193,603 per 
product. Where the service information lists required parts costs that 
are covered under warranty, we have assumed that there will be no 
charge for these parts. As we do not control warranty coverage for 
affected parties, some parties may incur costs higher than estimated 
here. Based on these figures, we estimate the cost of this AD to the 
U.S. operators to be $1,592,984, or $199,123 per product.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this AD will not have federalism implications 
under Executive Order 13132. This AD will not have a substantial direct 
effect 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.
    For the reasons discussed above, I certify this AD:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the 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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD docket.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Operations office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains the NPRM, the regulatory evaluation, 
any comments received, and other information. The street address for 
the Docket Operations office (telephone (800) 647-5527) is in the 
ADDRESSES section. Comments will be available in the AD docket shortly 
after receipt.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
2. The FAA amends Sec.  39.13 by removing Amendment 39-11098 (64 FR 
15659, April 1, 1999) and adding the following new AD:

2009-26-14 CONSTRUCCIONES AERONAUTICAS, S.A. (CASA): Amendment 39-
16153. Docket No. FAA-2009-0637; Directorate Identifier 2008-NM-183-
AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective February 
4, 2010.

Affected ADs

    (b) This AD supersedes AD 99-07-13, Amendment 39-11098.

Applicability

    (c) This AD applies to CASA Model CN-235, CN-235-100, CN-235-
200, and CN-235-300 airplanes, certificated in any category, all 
serial numbers, if part number (P/N) 35-15501-0001, -0002, -0003, or 
-0004, or P/N 35-A0736-0001 or -0002 outer flaps are installed.

Subject

    (d) Air Transport Association (ATA) of America Code 57: Wings.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:

    As a consequence of cracks [that were originally] detected on 
some CN-235 aircraft, in flap fittings P/N 35-15501-0101, -0102, -
0201 and -0202, attaching the structure of the outer flaps to their 
rear supports and, in the adjacent structure, DGAC Spain issued AD 
Nr. 01/97 which required, pending the analysis of the problem, 
boroscopic inspections of the attachment zones between both outer 
flaps to their rear support. After concluding that process and based 
on the investigation results, DGAC [Direcci[oacute]n General de 
Aviaci[oacute]n Civil] Spain issued AD Nr. 1/97 Rev.1 [which 
corresponds to FAA AD 99-07-13] to require the replacement of the 
outer flaps with new designed parts, as specified in EADS-CASA 
Service Bulletin (SB) 235-57-20.
    Since AD 1/97 Rev.1 was published, similar cracks have been 
detected in flaps longerons. EADS-CASA issued SB 235-57-20 Revision 
1, extending the scope of the inspection to these flaps longerons, 
instructing the drilling of holes to facilitate the inspection and 
introducing an improved outer flap replacement kit that included a 
new improved longeron. SB 235-57-20 Revision 2 has been issued to 
add useful references and to update the applicability.
    For the reasons described above, this new EASA [European 
Aviation Safety Agency] AD retains the requirements of DGAC Spain AD 
Nr. 1/97 Rev.1, which is superseded, and confirms the approval of 
additional outer flaps replacement options, as specified in 
paragraph 2 E.2 of EADS-CASA SB 235-57-20 R2.

Fatigue cracking of the rear internal support fittings and longerons 
of the outer flap

[[Page 69249]]

structure could result in failure of the outer flaps, and consequent 
reduced controllability of the airplane.

Actions and Compliance

    (f) Unless already done, do the following actions.
    (1) For airplanes equipped with P/N 35-A0736-0001 or -0002 outer 
flaps: Within 300 flight cycles after the effective date of this AD, 
do a borescopic inspection to detect cracking of the outer flaps 
fittings and longerons, in accordance with the Accomplishment 
Instructions of EADS-CASA Service Bulletin SB-235-57-20, Revision 2, 
dated March 30, 2007.
    (2) For airplanes equipped with P/N 35-15501-0001, -0002, -0003, 
or -0004 outer flaps: At the earlier of the times specified in 
paragraphs (f)(2)(i) and (f)(2)(ii) of this AD, do a borescopic 
inspection to detect cracking of the outer flaps fittings; and 
within 300 flight cycles after the effective date of this AD, do a 
borescopic inspection to detect cracking of the longerons. Do the 
inspections in accordance with the Accomplishment Instructions of 
EADS-CASA Service Bulletin SB-235-57-20, Revision 2, dated March 30, 
2007.
    (i) Within 600 flight cycles after the most recent inspection 
done in accordance with AD 99-07-13, or within 14 days after the 
effective date of this AD, whichever occurs later.
    (ii) Within 300 flight cycles after the effective date of this 
AD.
    (3) If, during any inspection required by paragraph (f)(1) or 
(f)(2) of this AD, no crack is detected, repeat the borescopic 
inspections of the outer flap fittings and longerons in accordance 
with the Accomplishment Instructions of EADS-CASA Service Bulletin 
SB-235-57-20, Revision 2, dated March 30, 2007, thereafter at 
intervals not to exceed 300 flight cycles or 6 months, whichever 
occurs first, until the replacement specified in paragraph (f)(4) or 
(f)(5) of this AD is accomplished.
    (4) If any crack is detected during any inspection required by 
paragraph (f)(1), (f)(2), or (f)(3) of this AD, prior to further 
flight, replace the outer flap with a new or retrofitted flap in 
accordance with the Accomplishment Instructions of EADS-CASA Service 
Bulletin SB-235-57-20, Revision 2, dated March 30, 2007. Such 
replacement constitutes terminating action for the repetitive 
borescopic inspection required by this AD for the replaced outer 
flap only.
    (5) For affected parts that have not been replaced in accordance 
with paragraph (f)(4) of this AD: At the later of the times 
specified in paragraphs (f)(5)(i) and (f)(5)(ii) of this AD, replace 
each outer flap with a new or retrofitted outer flap in accordance 
with the Accomplishment Instructions of EADS-CASA Service Bulletin 
SB-235-57-20, Revision 2, dated March 30, 2007. Replacing all outer 
flaps terminates the requirements of this AD.
    (i) Before the accumulation of 4,000 total flight cycles on the 
flap.
    (ii) Within 1,200 flight cycles or 24 months after the effective 
date of this AD, whichever occurs first.
    (6) Actions done before the effective date of this AD in 
accordance with CASA Service Bulletin SB-235-57-20, dated December 
23, 1997; or EADS-CASA Service Bulletin SB-235-57-20, Revision 1, 
dated April 30, 2004; are acceptable for compliance with the 
corresponding requirements of paragraph (f)(2) of this AD.

FAA AD Differences

    Note 1: This AD differs from the MCAI and/or service information 
as follows: No differences.

Other FAA AD Provisions

    (g) The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
has the authority to approve AMOCs for this AD, if requested using 
the procedures found in 14 CFR 39.19. Send information to ATTN: 
Shahram Daneshmandi, Aerospace Engineer, International Branch, ANM-
116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., 
Renton, Washington 98057-3356; telephone (425) 227-1112; fax (425) 
227-1149. Before using any approved AMOC on any airplane to which 
the AMOC applies, notify your principal maintenance inspector (PMI) 
or principal avionics inspector (PAI), as appropriate, or lacking a 
principal inspector, your local Flight Standards District Office. 
The AMOC approval letter must specifically reference this AD.
    (2) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer or other source, use these 
actions if they are FAA-approved. Corrective actions are considered 
FAA-approved if they are approved by the State of Design Authority 
(or their delegated agent). You are required to assure the product 
is airworthy before it is returned to service.
    (3) Reporting Requirements: For any reporting requirement in 
this AD, under the provisions of the Paperwork Reduction Act (44 
U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has 
approved the information collection requirements and has assigned 
OMB Control Number 2120-0056.

Related Information

    (h) Refer to MCAI EASA Airworthiness Directive 2008-0119, dated 
June 27, 2008; and EADS-CASA Service Bulletin SB-235-57-20, Revision 
2, dated March 30, 2007; for related information.

Material Incorporated by Reference

    (i) You must use EADS-CASA Service Bulletin SB-235-57-20, 
Revision 2, dated March 30, 2007, to do the actions required by this 
AD, unless the AD specifies otherwise.
    (1) The Director of the Federal Register approved the 
incorporation by reference of this service information under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) For service information identified in this AD, contact EADS-
CASA, Military Transport Aircraft Division (MTAD), Integrated 
Customer Services (ICS), Technical Services, Avenida de 
Arag[oacute]n 404, 28022 Madrid, Spain; telephone +34 91 585 55 84; 
fax +34 91 585 55 05; e-mail MTA.TechnicalService@casa.eads.net; 
Internet https://www.eads.net.
    (3) You may review copies of the service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington. For information on the availability of this material at 
the FAA, call 425-227-1221 or 425-227-1152.
    (4) You may also review copies of the service information that 
is incorporated by reference at the National Archives and Records 
Administration (NARA). For information on the availability of this 
material at NARA, call 202-741-6030, or go to: https://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on December 16, 2009.
Stephen P. Boyd,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E9-30707 Filed 12-30-09; 8:45 am]
BILLING CODE 4910-13-P

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