Federal Register / Vol. 77, No. 98 / Monday, May 21, 2012 / Rules and Regulations 29861 

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 me.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 


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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 


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

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 found 

free 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 


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