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to the manager of the ACO, send it to the attention of the person identified in the Related Information section of this AD. Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov.

(2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office.

(3) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) or other person who has been authorized by the Manager, Seattle ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically refer to this AD.

(4) AMOCs approved previously in accordance with AD 90–21–17, Amendment 39–6768 (55 FR 41510, October 12, 1990), are approved as AMOCs for the corresponding provisions of paragraphs (g) and (i) of this AD. AMOCs approved previously in accordance with AD 90–21–17, Amendment 39–6768 (55 FR 41510, October 12, 1990), are approved as AMOCs for the corresponding provisions of paragraphs (j) and (n) of this AD only if the repair or preventive modification of the affected lap splice was done in accordance with Boeing Service Bulletin 747–53A2303, Revision 2, dated October 1, 2009, including Boeing Designated Engineering Representative (DER) or Airworthiness Representative (AR) approvals of deviations to Boeing Service Bulletin 747– 53A2303, Revision 2, dated October 1, 2009.

(r) Related Information

For more information about this AD, contact Bill Ashforth, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, Washington 98057– 3356; telephone 425–917–6432; fax 425–917– 6590; email: bill.ashforth@faa.gov

. (s) Material Incorporated by Reference

(1) You must use the following service information to do the actions required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference (IBR) of the following service information under 5 U.S.C. 552(a) and 1 CFR part 51:

(i) Boeing Alert Service Bulletin 747– 53A2303, dated June 2, 1988.

(ii) Boeing Alert Service Bulletin 747– 53A2303, Revision 1, dated March 29, 1990.

(iii) Boeing Service Bulletin 747–53A2303, Revision 2, dated October 1, 2009.

(2) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, Washington 98124–2207; telephone 206–544–5000, extension 1; fax 206–766– 5680; email m e.boecom@boeing.com; Internet https://www.myboeingfleet.com.

(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.

(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 an NARA facility, call 202–741– 6030, or go to http://www.archives.gov/ federal

_register/code

_ of

_ federal

_regulations/ ibr

_ locations.html. Issued in Renton, Washington, on May 8,
2012. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2012–11869 Filed 5–18–12; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2012–0141; Directorate Identifier 2011–NM–092–AD; Amendment**  **39–17054; AD 2012–10–05]**

**RIN 2120–AA64**

**Airworthiness Directives; Fokker Services B.V. Airplanes** 

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

**ACTION :**  Final rule.

**SUMMARY :**  We are adopting a new airworthiness directive (AD) for all Fokker Services B.V. Model F.28 Mark 0070 and 0100 airplanes. This AD was prompted by an in-flight failure of the hydraulic control panel, which resulted in the absence of pressure and quantity indication of the hydraulic system and accompanying alerts for ‘‘hydraulic system 1 low quantity’’ and ‘‘hydraulic system 2 low quantity.’’ This AD requires implementing new abnormal procedures for hydraulics in the airplane flight manual (AFM). We are issuing this AD to prevent loss of control of the airplane due to incorrect hydraulic system failure information being provided to the flightcrew, followed by application of inappropriate procedures.

**DATES :**  This AD becomes effective June 25, 2012.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of June 25, 2012.

**ADDRESSES :**  You may examine the AD docket on the Internet at http:// 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 :**  Tom Rodriguez, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057–3356; telephone (425) 227–1137; 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 February 14, 2012 (77 FR 8181). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states:

An in-flight failure of the hydraulic control panel resulted in the absence of pressure and quantity indication of the hydraulic system and accompanying alerts for ‘‘hydraulic system 1 low quantity’’ and ‘‘hydraulic system 2 low quantity’’. The procedures prescribed the shut-off of the engine driven hydraulic pumps, resulting in complete absence of hydraulic pressure, which made it impossible to hydraulically control the flight controls, including the stabiliser. The status information contained in the procedures for these alerts may give the false impression that the stabiliser is still hydraulically controllable on one channel. The flight crew regained control by using the alternate electrically powered stabiliser control.

A safety review revealed that a ‘‘hydraulic system 1 and 2 low quantity’’ alert could give the right information, however this alert is not available in the Flight Warning System. To solve this problem, Fokker Services improved the Hydraulic 1(2) Low Quantity Procedures in the Airplane Flight Manual (AFM).

For the reasons described above, this [EASA] AD requires the implementation of new abnormal procedures for hydraulics in the AFM. The unsafe condition is possible loss of control of the airplane due to incorrect hydraulic system failure information being provided to the flightcrew, followed by application of inappropriate procedures. 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 (77 FR 8181, February 14, 2012) 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


### 29862 Federal Register / Vol. 77, No. 98 / Monday, May 21, 2012 / Rules and Regulations

as proposed, except for minor editorial changes. We have determined that these minor changes:

• Are consistent with the intent that was proposed in the NPRM (77 FR 8181, February 14, 2012) for correcting the unsafe condition; and

• Do not add any additional burden upon the public than was already proposed in the NPRM (77 FR 8181, February 14, 2012). Costs of Compliance

We estimate that this AD will affect about 4 products of U.S. registry. We also estimate that it will take about 1 work-hour per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this AD to the U.S. operators to be $340, or $85 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 that 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);

3. Will not affect intrastate aviation in Alaska; and

4. 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 http:// 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 (77 FR 8181, February 14, 2012), 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:

Authority: 49 U.S.C. 106(g), 40113, 44701.

**§ 39.13 [Amended]**

■ 2. The FAA amends § 39.13 by adding the following new AD:

2012–10–05 Fokker Services B.V.: Amendment 39–17054. Docket No. FAA–2012–0141; Directorate Identifier 2011–NM–092–AD.
(a) Effective Date

This airworthiness directive (AD) becomes effective June 25, 2012.

(b) Affected ADs

None. (c) Applicability

This AD applies to Fokker Services B.V. Model F.28 Mark 0070 and 0100 airplanes, certificated in any category, all serial numbers.
(d) Subject

Air Transport Association (ATA) of America Code 29, Hydraulic power.

(e) Reason

This AD was prompted by an in-flight failure of the hydraulic control panel, which resulted in the absence of pressure and quantity indication of the hydraulic system and accompanying alerts for ‘‘hydraulic system 1 low quantity’’ and ‘‘hydraulic system 2 low quantity.’’ We are issuing this AD to prevent loss of control of the airplane due to incorrect hydraulic system failure information being provided to the flightcrew, followed by application of inappropriate procedures.
(f) Compliance

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
(g) Airplane Flight Manual (AFM) Revision

Within 3 months after the effective date of this AD, revise the Abnormal Procedures— Hydraulics section of the Fokker F.28 AFM by incorporating the information specified in Fokker Manual Change Notification— Operational Documentation (MCNO) MCNO– F100–057, dated December 17, 2010, into the Abnormal Procedures—Hydraulics section of the AFM.

Note 1 to paragraph (g) of this AD: The actions required by paragraph (g) of this AD may be done by inserting a copy of Fokker MCNO MCNO–F100–057, dated December 17, 2010, into the Abnormal Procedures— Hydraulics section of the Fokker F.28 AFM. When Fokker MCNO MCNO–F100–057, dated December 17, 2010, has been included in the general revisions of the AFM, the general revisions may be inserted in the AFM, provided the relevant information in the general revision is identical to that in Fokker MCNO MCNO–F100–057, dated December 17, 2010, and that MCNO may be removed.

(h) Other FAA AD Provisions

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. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to Attn: Tom Rodriguez, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057– 3356; telephone (425) 227–1137; fax (425) 227–1149. Information may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding 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


### 29863 Federal Register / Vol. 77, No. 98 / Monday, May 21, 2012 / Rules and Regulations

to assure the product is airworthy before it is returned to service.
(i) Related Information

Refer to MCAI European Aviation Safety Agency (EASA) Airworthiness Directive 2011–0051, dated March 22, 2011; and Fokker MCNO MCNO–F100–057, dated December 17, 2010; for related information.
(j) Material Incorporated by Reference

(1) The Director of the Federal Register approved the incorporation by reference (IBR) of the following service information under 5 U.S.C. 552(a) and 1 CFR part 51.

(2) You must use the following service information to do the actions required by this AD, unless the AD specifies otherwise.

(i) Fokker Manual Change Notification— Operational Documentation MCNO–F100– 057, dated December 17, 2010.

(3) For service information identified in this AD, contact Fokker Services B.V., Technical Services Dept., P.O. Box 231, 2150 AE Nieuw-Vennep, the Netherlands; telephone +31 (0)252–627–350; fax +31 (0)252–627–211; email technicalservices. fokkerservices@stork.com; Internet http:// www.myfokkerfleet.com.

(4) 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.

(5) 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 an NARA facility, call 202–741– 6030, or go to http://www.archives.gov/ federal

_ register/code

_ of

_ federal

_ regulations/ ibr

_ locations.html. Issued in Renton, Washington, on May 9,
2012. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2012–11954 Filed 5–18–12; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2012–0534; Directorate Identifier 2012–CE–015–AD; Amendment**  **39–17053; AD 2012–10–04]**

**RIN 2120–AA64**

**Airworthiness Directives; Cessna Aircraft Company Airplanes** 

**AGENCY :**  Federal Aviation Administration (FAA), DOT.

**ACTION :**  Final rule; request for
comments.

**SUMMARY :**  We are adopting a new airworthiness directive (AD) for certain Cessna Aircraft Company Models 210G, T210G, 210H, T210H, 210J, T210J, 210K, T210K, 210L, T210L, 210M, T210M, 210N, T210N, P210N, 210R, T210R, and P210R airplanes. This AD requires an inspection(s) of the left and right wing lower main spar caps for cracks and either replacing cracked wing lower main spar caps, wing spars, or wings (as applicable) with serviceable spar caps, spars, or wings that are foundfree of cracks or incorporating an FAAapproved modification. This AD also requires reporting the results of the inspections to the FAA. This AD was prompted by reports of cracks found in the wing lower main spar caps on the above-referenced airplanes with cantilever metal wings. We are issuing this AD to correct the unsafe condition on these products.

**DATES :**  This AD is effective June 5, 2012.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of June 5, 2012.

We must receive comments on this AD by July 5, 2012.

**ADDRESSES :**  You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods:

• Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.

• Fax: 202–493–2251.

• Mail: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590.

• Hand Delivery: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

For service information identified in this AD, contact Cessna Aircraft Company, Customer Support Service, P.O. Box 7706, Wichita, Kansas 67277; telephone: (316) 517–5800; fax (316) 517–7271; Internet: www.cessnasupport.com . You may review copies of the referenced service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329–4148. Examining the AD Docket

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

**FOR FURTHER INFORMATION CONTACT :**  Gary D. Park, Aerospace Engineer, Wichita Aircraft Certification Office, (ACO), FAA, 1801 Airport Road, Wichita, KS 67209; phone: (316) 946–4123; fax: (316) 946–4107; email: WICHITACOS@FAA.GOV

. **SUPPLEMENTARY INFORMATION :** 

Discussion

We received reports of cracks found in the wing lower main spar caps on Cessna Aircraft Company Models 210G, T210G, 210H, T210H, 210J, T210J, 210K, T210K, 210L, T210L, 210M, T210M, 210N, T210N, P210N, 210R, T210R, and P210R airplanes with cantilever metal wings. The reports include a wing lower main spar cap that was completely severed with the skin split. This condition, if not corrected, could result in structural failure of the wing with consequent loss of control.

Relevant Service Information

We reviewed Cessna Aircraft Company Single Engine Service Letter SEL–57–01, Revision 1, dated May 9, 2012. The service letter describes procedures for visually inspecting the right and left lower main spar caps for cracks and replacing the spar cap, wing spar, or wing, as applicable.

FAA’s Determination

We are issuing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design.
AD Requirements

This AD requires a one-time internal (for all airplanes) and external (for certain airplanes) visual inspection of the left and right wing lower main spar caps for cracks and either replacing cracked wing lower main spar caps, wing spars, or wings, or incorporating an FAA-approved modification. This AD also requires reporting the results of the inspections to the FAA, Wichita ACO.

Interim Action

We consider this AD interim action. We are requiring inspection(s) of the left and right wing lower main spar caps with a report to the FAA of the results. We will work with the type certificate