Federal Register / Vol. 77, No. 54 / Tuesday, March 20, 2012 / Rules and Regulations 16145 

under the criteria of the Regulatory 

Flexibility Act. 

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 airworthiness 

directive (AD): 

2012–05–03 The Boeing Company: 

Amendment 39–16975; Docket No. 

FAA–2011–0566; Directorate Identifier 

2010–NM–271–AD. 

(a) Effective Date 

This AD is effective April 24, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 747–100, 747–100B, 747–100B SUD, 

747–200B, 747–200C, 747–200F, 747–300, 

747–400, 747–400D, 747–400F, 747SR, and 

747SP series airplanes, certificated in any 

category, as identified in Boeing Special 

Attention Service Bulletin 747–57–2332, 

Revision 1, dated July 25, 2011. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 57, Wings. 

(e) Unsafe Condition 

This AD was prompted by a design review 

following a ground fire incident and reports 

of flammable fluid leaks from the wing 

leading edge area onto the engine exhaust 

area. We are issuing this AD to prevent 

flammable fluid from leaking onto the engine 

exhaust nozzle, which could result in a fire. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Leading Edge Installation 

Within 60 months after the effective date 

of this AD, modify the fluid drain path in the 

leading edge area of the wing, in accordance 

with the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

747–57–2332, Revision 1, dated July 25, 

2011. 

(h) Credit for Previous Actions 

This paragraph provides credit for 

modifications of the fluid drain path required 

by paragraph (g) of this AD, if the 

modification was performed before the 

effective date of this AD, using Boeing 

Special Attention Service Bulletin 747–57– 

2332, dated November 9, 2010. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), 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 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 structural 

repairs required by this AD if it is approved 

by the Boeing Commercial Airplanes 

Organization Designation Authorization 

(ODA) that 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. 

(j) Related Information 

For more information about this AD, 

contact Tung Tran, Aerospace Engineer, 

Propulsion Branch, ANM–140S, Seattle 

Aircraft Certification Office (ACO), FAA, 

1601 Lind Avenue SW., Renton, Washington 

98057–3356; phone: 425–917–6505; fax: 425– 

917–6590; email: Tung.Tran@faa.gov. 

(k) 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 under 5 U.S.C. 552(a) and 1 CFR 

part 51: 

(i) Boeing Special Attention Service 

Bulletin 747–57–2332, Revision 1, dated July 

25, 2011. 

(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; phone: 

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 

referenced 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 NARA, call 202–741–6030, or go 

to: http://www.archives.gov/federal-register/ 

cfr/ibr-locations.html. 

Issued in Renton, Washington, on February 

27, 2012. 

Jeffrey E. Duven, 

Acting Manager. Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–6116 Filed 3–19–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0190; Directorate 

Identifier 2012–NM–033–AD; Amendment 

39–16979; AD 2012–05–07] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Bombardier, Inc. Model DHC–8–102, 

–103, and –106 airplanes. This AD 

requires a general visual inspection for 

chamfer of the upper edge of each leaf 

spring, and rework if necessary. This 

AD also requires installing a new 

friction brake nut. This AD was 

prompted by reports that it was possible 

to inadvertently move the power levers 

through the flight idle gate into the beta 

range due to an un-chamfered leaf 

spring in the friction brake that may 

contact the power lever latch when the 

friction adjusting knob is fully loosened. 

We are issuing this AD to detect and 

correct an unsafe condition where both 

engines can inadvertently be operated in 

beta mode during flight and 

consequently reduce controllability of 

the airplane. 

DATES: This AD becomes effective April 

4, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of April 4, 2012. 

We must receive comments on this 

AD by May 4, 2012. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 


wreier-aviles on DSK5TPTVN1PROD with RULES
16146 Federal Register / Vol. 77, No. 54 / Tuesday, March 20, 2012 / Rules and Regulations 

• 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, between 9 a.m. and 

5 p.m., Monday through Friday, except 

Federal holidays. 

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 this AD, 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. 

FOR FURTHER INFORMATION CONTACT: 

Mazdak Hobbi, Aerospace Engineer, 

Propulsion and Services Branch, ANE– 

173, FAA, New York Aircraft 

Certification Office, 1600 Stewart 

Avenue Suite 410, Westbury, NY 11590; 

telephone (516) 228–7330; fax (516) 

794–5531. 

SUPPLEMENTARY INFORMATION: 

Discussion 

Transport Canada Civil Aviation 

(TCCA) which is the aviation authority 

for Canada, has issued Canadian 

Emergency Airworthiness Directive CF– 

2012–08, dated January 30, 2012 

(referred to after this as ‘‘the MCAI’’), to 

correct an unsafe condition for the 

specified products. The MCAI states: 

During maintenance, it was discovered that 

it was possible to inadvertently move the 

power levers through the flight idle gate into 

the beta range. An investigation revealed that 

an un-chamfered leaf spring in the friction 

brake may contact the power lever latch 

when the friction adjusting knob is fully 

loosened. This can result in the lifting of the 

power lever latch and allow the power levers 

to pass through the flight idle gate without 

lifting the triggers. 

Further investigation also determined that 

an un-chamfered spring installation with a 

pre-Service Bulletin (SB) 8–76–2 

(Modification 8/0443) friction brake nut can 

further increase the possibility of allowing 

power levers to pass through the flight idle 

gate without lifting the triggers, when the 

friction adjusting knob is fully loosened. 

The above discrepancies, if not corrected, 

may result in an unsafe condition where both 

engines can inadvertently be operated in beta 

mode during flight. 

In order to address this potentially unsafe 

condition, Bombardier has issued: 

• Alert Service Bulletin (ASB) A8–76–32 

requiring operators to inspect [general visual 

inspection] the springs and chamfer [rework] 

the springs as applicable, and 

• SB 8–76–02 Rev. A to replace the pre-SB 

8–76–2 (Mod 8/0443) original friction brake 

nut with a new friction brake nut with larger 

shoulders. 

This [TCCA] Airworthiness Directive (AD) 

is being issued to mandate compliance with 

Bombardier ASB A8–76–32 and SB 8–76–02 

Rev. A requirements on the affected 

aeroplanes. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Bombardier has issued the following 

service bulletins: 

• Alert Service Bulletin A8–76–32, 

dated January 27, 2012. 

• Service Bulletin 8–76–02, Revision 

‘‘A,’’ dated January 25, 2012. 

The actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. 

FAA’s Determination and Requirements 

of this AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are issuing this 

AD because we evaluated all pertinent 

information and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

FAA’s Determination of the Effective 

Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD. The FAA has found that the risk to 

the flying public justifies waiving notice 

and comment prior to adoption of this 

rule because there have been reports 

that it was possible to inadvertently 

move the power levers through the 

flight idle gate into the beta range due 

to an un-chamfered leaf spring in the 

friction brake that may contact the 

power lever latch when the friction 

adjusting knob is fully loosened. This 

can result in the lifting of the power 

lever latch and allow the power levers 

to pass through the flight idle gate 

without lifting the triggers. Also, a 

certain un-chamfered spring installation 

with a friction brake nut can further 

increase the possibility of allowing 

power levers to pass through the flight 

idle gate without lifting the triggers, 

when the friction adjusting knob is fully 

loosened. These conditions, if not 

corrected, may result in an unsafe 

condition where both engines can 

inadvertently be operated in beta mode 

during flight and consequently reduce 

controllability of the airplane. 

Therefore, we determined that notice 

and opportunity for public comment 

before issuing this AD are impracticable 

and that good cause exists for making 

this amendment effective in fewer than 

30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not precede it by notice and 

opportunity for public comment. We 

invite you to send any written relevant 

data, views, or arguments about this AD. 

Send your comments to an address 

listed under the ADDRESSES section. 

Include ‘‘Docket No. FAA–2012–0190; 

Directorate Identifier 2012–NM–033– 

AD’’ at the beginning of your comments. 

We specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this AD because of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this AD. 

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. 


wreier-aviles on DSK5TPTVN1PROD with RULES
Federal Register / Vol. 77, No. 54 / Tuesday, March 20, 2012 / Rules and Regulations 16147 

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. 

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: 

2012–05–07 Bombardier, Inc.: Amendment 

39–16979. Docket No. FAA–2012–0190; 

Directorate Identifier 2012–NM–033–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective April 4, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Bombardier, Inc. Model 

DHC–8–102, –103, and –106 airplanes, 

certificated in any category, serial numbers 

003 through 039 inclusive. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 76: Engine Controls. 

(e) Reason 

This AD was prompted by reports that it 

was possible to inadvertently move the 

power levers through the flight idle gate into 

the beta range due to an un-chamfered leaf 

spring in the friction brake that may contact 

the power lever latch when the friction 

adjusting knob is fully loosened. We are 

issuing this AD to detect and correct an 

unsafe condition where both engines can 

inadvertently be operated in beta mode 

during flight and consequently reduce 

controllability of the airplane. 

(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) Actions 

Within 50 flight hours or 10 days, 

whichever occurs first, after the effective date 

of this AD, do the actions specified in 

paragraphs (g)(1) and (g)(2) of this AD. 

(1) Do a general visual inspection of the 

upper edge of each leaf spring for chamfer, 

in accordance with the Accomplishment 

Instructions of Bombardier Alert Service 

Bulletin A8–76–32, dated January 27, 2012. 

Do all applicable rework before further flight, 

in accordance with the Accomplishment 

Instructions of Bombardier Alert Service 

Bulletin A8–76–32, dated January 27, 2012. 

(2) Install a new friction brake nut, in 

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

8–76–02, Revision ‘A,’ dated January 25, 

2012. 

(h) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

Certification Office (ACO), ANE–170, 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 ACO, send it to ATTN: 

Program Manager, Continuing Operational 

Safety, FAA, New York ACO, 1600 Stewart 

Avenue, Suite 410, Westbury, New York 

11590; telephone 516–228–7300; fax 516– 

794–5531. 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 

to assure the product is airworthy before it 

is returned to service. 

(i) Related Information 

Refer to MCAI Canadian Airworthiness 

Directive CF–2012–08, dated January 30, 

2012; Bombardier Alert Service Bulletin A8– 

76–32, dated January 27, 2012; and 

Bombardier Service Bulletin 8–76–02, 

Revision ‘A,’ dated January 25, 2012; for 

related information. 

(j) 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) Bombardier Alert Service Bulletin A8– 

76–32, dated January 27, 2012. 

(ii) Bombardier Service Bulletin 8–76–02, 

Revision ‘‘A,’’ dated January 25, 2012. 

(2) For service information identified in 

this AD, contact Bombardier, Inc., Q–Series 

Technical Help Desk, 123 Garratt Boulevard, 

Toronto, Ontario M3K 1Y5, Canada; 

telephone 416–375–4000; fax 416–375–4539; 

email thd.qseries@aero.bombardier.com; 

Internet http://www.bombardier.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 March 2, 

2012. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–6439 Filed 3–19–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–27223; Directorate 

Identifier 2006–NM–224–AD; Amendment 

39–16976; AD 2012–05–04] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 767 

airplanes. This AD requires an 

inspection of the number 2 windows to 


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