This section of the FEDERAL REGISTER

contains notices to the public of the proposed

issuance of rules and regulations. The

purpose of these notices is to give interested

persons an opportunity to participate in the

rule making prior to the adoption of the final

rules.

Proposed Rules Federal Register

71470 

Vol. 76, No. 223 

Friday, November 18, 2011 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1230; Directorate 

Identifier 2011–NM–141–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for Model 

DHC–8–102, –103, and –106 airplanes 

and Model DHC–8–200, –300, and –400 

series airplanes. This proposed 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: 

Several reports have been received 

regarding cracking of the DHC–8 Series 100 

rudder actuator mounting bracket. An 

investigation revealed that the mounting 

bracket has been under-designed based on 

the static and endurance loading conditions. 

The failure of the mounting brackets that 

attach the power control unit (PCU) to the 

airframe could result in a loss of the rudder 

actuating system. The loss of both rudder 

PCU actuators could result in free play of the 

rudder control surface and potentially induce 

a flutter condition. 

* * * * * 

The unsafe condition is loss of 

controllability of the airplane. The 

proposed AD would require actions that 

are intended to address the unsafe 

condition described in the MCAI. 

DATES: We must receive comments on 

this proposed AD by January 3, 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. 

• 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. 

For service information identified in 

this proposed 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. 

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. 

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 proposed 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: 

Cesar Gomez, Aerospace Engineer, 

Airframe and Mechanical Systems 

Branch, ANE–171, FAA, New York 

Aircraft Certification Office (ACO), 1600 

Stewart Avenue, Suite 410, Westbury, 

New York 11590; telephone (516) 228– 

7318; fax (516) 794–5531. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2011–1230; Directorate Identifier 

2011–NM–141–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on 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 proposed AD. 

Discussion 

Transport Canada Civil Aviation, 

which is the aviation authority for 

Canada, has issued Canadian 

Airworthiness Directive CF–2011–12, 

dated June 6, 2011 (referred to after this 

as ‘‘the MCAI’’), to correct an unsafe 

condition for the specified products. 

The MCAI states: 

Several reports have been received 

regarding cracking of the DHC–8 Series 100 

rudder actuator mounting bracket. An 

investigation revealed that the mounting 

bracket has been under-designed based on 

the static and endurance loading conditions. 

The failure of the mounting brackets that 

attach the power control unit (PCU) to the 

airframe could result in a loss of the rudder 

actuating system. The loss of both rudder 

PCU actuators could result in free play of the 

rudder control surface and potentially induce 

a flutter condition. 

This [TCCA] directive mandates the 

installation of a new design of rudder 

actuator mounting bracket [adapter]. 

The unsafe condition is loss of 

controllability of the airplane. You may 

obtain further information by examining 

the MCAI in the AD docket. 

Relevant Service Information 

Bombardier has issued Service 

Bulletins 8–27–110, Revision C, dated 

May 13, 2011; and 84–27–53, dated 

November 26, 2010. 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 Proposed 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 


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Federal Register / Vol. 76, No. 223 / Friday, November 18, 2011 / Proposed Rules 71471 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

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 proposed 

different actions in this AD from those 

in the MCAI in order to follow FAA 

policies. Any such differences are 

highlighted in a NOTE within the 

proposed AD. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 171 products of U.S. 

registry. We also estimate that it would 

take up to 10 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Required 

parts would cost up to $2,856 per 

product. Based on these figures, we 

estimate the cost of the proposed AD on 

U.S. operators to be up to $633,726, or 

$3,706 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 proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would 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 proposed regulation: 

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 proposed 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. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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: 

Bombardier, Inc.: Docket No. FAA–2011– 

1230; Directorate Identifier 2011–NM– 

141–AD. 

Comments Due Date 

(a) We must receive comments by January 

3, 2012. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Bombardier, Inc. 

airplanes identified in paragraphs (c)(1) and 

(c)(2) of this AD, certificated in any category. 

(1) Model DHC–8–102, –103, –106, –201, 

–202, –301, –311, and –315 airplanes, serial 

numbers 003 through 672 inclusive. 

(2) Model DHC–8–400, –401, and –402 

airplanes, serial numbers 4001 through 4343 

inclusive. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 27: Flight controls. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

Several reports have been received 

regarding cracking of the DHC–8 Series 100 

rudder actuator mounting bracket. An 

investigation revealed that the mounting 

bracket has been under-designed based on 

the static and endurance loading conditions. 

The failure of the mounting brackets that 

attach the power control unit (PCU) to the 

airframe could result in a loss of the rudder 

actuating system. The loss of both rudder 

PCU actuators could result in free play of the 

rudder control surface and potentially induce 

a flutter condition. 

* * * * * 

The unsafe condition is loss of controllability 

of the airplane. 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Free-Play Check and Corrective Actions 

(g) Within 6,000 flight hours or 3 years 

after the effective date of this AD, whichever 

occurs first, do the actions required by 

paragraph (g)(1) or (g)(2) of this AD, as 

applicable. 

(1) For Model DHC–8–102, –103, –106, 

–201, –202, –301, –311, and –315 airplanes: 

Install a new CRES mounting adapter with 

new bolts by incorporating MODSUM 

8Q101890, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 8–27–110, Revision C, dated 

May 13, 2011. 

(2) For DHC–8–400, –401, and –402 

airplanes: Replace the existing upper and 

lower mounting adapters of the PCU with 

redesigned adapters by incorporating 

MODSUM 4–113655, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–27–53, dated November 

26, 2010. 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(h) Actions accomplished before the 

effective date of this AD in accordance with 

Bombardier Service Bulletins 8–27–110, 

Revision A, dated December 3, 2010, and 

Revision B, dated January 31, 2011, are 

considered acceptable for compliance with 

the corresponding actions specified in 

paragraph (g)(1) 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 

(i) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York ACO, 

ANE–170, FAA, has the authority to approve 


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71472 Federal Register / Vol. 76, No. 223 / Friday, November 18, 2011 / Proposed Rules 

AMOCs for this AD, if requested using the 

procedures found in 14 CFR 39.19. Send 

information 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. 

Related Information 

(j) Refer to MCAI Canadian Airworthiness 

Directive CF–2011–12, dated June 6, 2011; 

Bombardier Service Bulletin 8–27–110, 

Revision C, dated May 13, 2011; and 

Bombardier Service Bulletin 84–27–53, dated 

November 26, 2010; for related information. 

Issued in Renton, Washington, on 

November 7, 2011. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate Aircraft Certification Service. 

[FR Doc. 2011–29798 Filed 11–17–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1231; Directorate 

Identifier 2011–NM–088–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 737–600, 

–700, –700C, –800, –900, and –900ER 

series airplanes. This proposed AD 

would require inspecting to detect 

damage to the upper fire seals on the 

forward edge of the thrust reverser, 

where the fire seal contacts the 12- 

o’clock engine strut, and for correct 

stiffness and vent holes, and doing 

corrective actions if necessary; and 

installing a bracket for the fire seal. This 

proposed AD was prompted by reports 

of damaged fire seals on the forward 

edge of the thrust reverser. We are 

proposing this AD to detect and correct 

damage to the fire seals, which could 

result in damage to the strut structure 

and the thrust reverser firewall. Such 

damage could significantly deteriorate 

the protection capacity of the fire 

extinguishing system and result in an 

uncontrolled fire. 

DATES: We must receive comments on 

this proposed AD by January 3, 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. 

• 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 proposed 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. 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. 

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 proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket 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: 

Chris R. Parker, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; phone: (425) 

917–6496; fax: (425) 917–6590; email: 

chris.r.parker@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2011–1231; Directorate Identifier 

2011–NM–088–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed 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 proposed AD. 

Discussion 

We have received reports of damaged 

fire seals on the forward edge of the 

thrust reverser, where the fire seal 

contacts the 12-o’clock engine strut. The 

damage has been reported as light wear 

marks, tears, and holes in the bulb-part 

of the fire seal. The damage to the seal 

is attributed to insufficient seal stiffness 

and/or missing vent holes. If a damaged 

seal remained in service for an extended 

time, damage also could result to the 12- 

o’clock strut structure and the thrust 

reverser firewall. Such damage could 

significantly deteriorate the protection 

capacity of the fire extinguishing system 

and result in an uncontrolled fire. 

Relevant Service Information 

We have reviewed Boeing Special 

Attention Service Bulletin 737–78– 

1086, dated October 6, 2010. This 

service information describes 

procedures for a general visual 

inspection on the upper fire seals on the 

forward edge of the thrust reversers, 

where the fire seals contact the 12- 

o’clock engine strut, for damage and 

correct stiffness, and for sufficient vent 

holes behind the upper fire seals; and 

corrective actions if necessary. 

Corrective actions include replacing any 

damaged fire seal, drilling vent holes in 

the upper fire seal if needed. The 

service information also specifies 

installing a new bracket behind the fire 

seal retainer to further stiffen the seal. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 


jlentini on DSK4TPTVN1PROD with PROPOSALS