21820 Federal Register / Vol. 76, No. 75 / Tuesday, April 19, 2011 / Proposed Rules 

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: 

The Boeing Company: Docket No. FAA– 

2008–0415; Directorate Identifier 2007– 

NM–256–AD. 

Comments Due Date 

(a) We must receive comments by May 16, 

2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to all Model 737 

airplanes; certificated in any category. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 27: Flight controls. 

Unsafe Condition 

(e) This AD results from a report of 

extensive corrosion of a ballscrew in the 

drive mechanism of the horizontal stabilizer 

trim actuator (HSTA). We are issuing this AD 

to prevent an undetected failure of the 

primary load path for the ballscrew in the 

drive mechanism of the HSTA and 

subsequent wear and failure of the secondary 

load path, which could lead to loss of control 

of the horizontal stabilizer and consequent 

loss of control 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. 

Inspections, Lubrications, Repairs/ 

Overhauls, and Applicable Corrective 

Actions 

(g) At the applicable compliance time and 

repeat intervals listed in Tables 1 and 2 of 

paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert 

Service Bulletin 737–27A1278, Revision 1, 

dated January 7, 2010; or Boeing Alert 

Service Bulletin 737–27A1277, Revision 2, 

dated January 8, 2010; as applicable 

(depending on airplane configuration): Do 

the inspections, lubrications, repairs/ 

overhauls, installation(s), and applicable 

corrective actions, by accomplishing all the 

applicable actions specified in the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–27A1278, Revision 1, 

dated January 7, 2010; or Boeing Alert 

Service Bulletin 737–27A1277, Revision 2, 

dated January 8, 2010; as applicable; except 

as provided by paragraphs (g)(1) and (g)(2) of 

this AD. 

Note 1: Boeing Alert Service Bulletin 737– 

27A1278, Revision 1, dated January 7, 2010; 

refers to Umbra Cuscinetti Service Bulletin 

07322–27–01, dated December 21, 2004; 

Linear Motion Service Bulletin 7901708, 

Revision A, or Revision B, both dated July 26, 

2005; Boeing 737 Service Bulletin 27–1046, 

Revision 1, dated April 5, 1974; and 

Skytronics Service Bulletin 93004, dated 

September 1, 2005; as applicable; as 

additional sources of service information for 

accomplishing the applicable specified 

actions. 

Note 2: Boeing Alert Service Bulletin 737– 

27A1277, Revision 2, dated January 8, 2010; 

refers to Umbra Cuscinetti Service Bulletin 

07322–27–01, dated December 21, 2004; as 

an additional source of service information 

for accomplishing the applicable specified 

actions. 

(1) Where paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 737–27A1278, 

Revision 1, dated January 7, 2010; or Boeing 

Alert Service Bulletin 737–27A1277, 

Revision 2, dated January 8, 2010; as 

applicable; specifies an initial compliance 

time for accomplishing the initial inspection, 

lubrication, or repair/overhaul, this AD 

requires doing the applicable initial action(s) 

at the later of the times specified in 

paragraphs (g)(1)(i) and (g)(1)(ii) of this AD. 

(i) At the applicable compliance time 

specified in paragraph 1.E, ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 737–27A1278, 

Revision 1, dated January 7, 2010; or Boeing 

Alert Service Bulletin 737–27A1277, 

Revision 2, dated January 8, 2010; as 

applicable. 

(ii) Within the applicable compliance time 

specified in paragraph (g)(1)(ii)(A), 

(g)(1)(ii)(B), or (g)(1)(ii)(C) of this AD. 

(A) For the initial detailed inspection and 

lubrication: Within 6 months after the 

effective date of this AD. 

(B) For the initial repair/overhaul: Within 

12 months after the effective date of this AD. 

(C) For the installation(s): Within 12 

months after the effective date of this AD. 

(2) Where Table 2 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–27A1277, Revision 2, dated 

January 8, 2010, specifies a compliance time 

of ‘‘* * * within 25,000 Flight Hours since 

the latest horizontal stabilizer trim actuator 

(HSTA) Overhaul from the date of Revision 

1 of this Service Bulletin * * *,’’ this AD 

requires compliance within 25,000 flight 

hours since the last overhaul of the trim 

actuator of the horizontal stabilizer. 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(h) Actions accomplished before the 

effective date of this AD in accordance with 

Boeing Alert Service Bulletins 737–27A1277, 

Revision 1, dated July 25, 2007; or 737– 

27A1278, dated May 24, 2007; as applicable; 

are considered acceptable for compliance 

with the corresponding actions specified in 

this AD. 

Parts Installation 

(i) As of the effective date of this AD, no 

person may install a ballscrew assembly in 

the drive mechanism of the HSTA on any 

airplane, unless it has been inspected and 

modified, as applicable, in accordance with 

paragraph (g) of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(j)(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 e-mailed 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) 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. 

Related Information 

(k) For more information about this AD, 

contact Kelly McGuckin, Aerospace 

Engineer, Systems and Equipment Branch, 

ANM–130S, FAA, Seattle Aircraft 

Certification Office, 1601 Lind Avenue, SW., 

Renton, Washington 98057–3356; telephone 

(425) 917–6490; fax (425) 917–6590. 

Issued in Renton, Washington, on April 13, 

2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–9410 Filed 4–18–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0381; Directorate 

Identifier 2010–NM–203–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Model DHC–8–400 Series 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above. This proposed 

AD results from mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country to identify and correct 


jdjones on DSK8KYBLC1PROD with PROPOSALS-1
Federal Register / Vol. 76, No. 75 / Tuesday, April 19, 2011 / Proposed Rules 21821 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

Several reports have been received on 

failures of the main landing gear (MLG) 

stabilizer extension springs. A landing gear 

audit has confirmed that the MLG may not 

lock in the down-lock position with the 

absence of both MLG stabilizer extension 

springs. The loss of the locking mechanism 

could result in the collapse of the main 

landing gear. 

* * * * * 

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 June 3, 2011. 

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 W12–40, 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; e-mail 

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: 

Fabio Buttitta, Aerospace Engineer, 

Airframe and Mechanical Systems 

Branch, ANE–171, FAA, New York 

Aircraft Certification Office, 1600 

Stewart Avenue, Suite 410, Westbury, 

New York 11590; telephone (516) 228– 

7303; 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–2011–0381; Directorate Identifier 

2010–NM–203–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 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2010–22, 

dated July 20, 2010 (referred to after this 

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

condition for the specified products. 

The MCAI states: 

Several reports have been received on 

failures of the main landing gear (MLG) 

stabilizer extension springs. A landing gear 

audit has confirmed that the MLG may not 

lock in the down-lock position with the 

absence of both MLG stabilizer extension 

springs. The loss of the locking mechanism 

could result in the collapse of the main 

landing gear. 

This [TCCA] directive is to mandate the 

incorporation of a new maintenance task for 

the MLG stabilizer extension springs. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Bombardier has issued Temporary 

Revision MRB–45, dated October 6, 

2009 to Section 1–32, Systems/ 

Powerplant Maintenance Program of 

Part 1 of the Maintenance Review Board 

(MRB) Report of the Bombardier Q400 

Dash 8 Maintenance Requirements 

Manual, PSM 1–84–7. 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 

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 65 products of U.S. registry. 

We also estimate that it would take 

about 1 work-hour per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Based on 

these figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$5,525, 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 


jdjones on DSK8KYBLC1PROD with PROPOSALS-1
21822 Federal Register / Vol. 76, No. 75 / Tuesday, April 19, 2011 / Proposed Rules 

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– 

0381; Directorate Identifier 2010–NM– 

203–AD. 

Comments Due Date 

(a) We must receive comments by June 3, 

2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Bombardier, Inc. 

Model DHC–8–400, –401, and –402 

airplanes, certificated in any category, serial 

numbers 4001, 4003 and subsequent. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 32: Landing Gear. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

Several reports have been received on 

failures of the main landing gear (MLG) 

stabilizer extension springs. A landing gear 

audit has confirmed that the MLG may not 

lock in the down-lock position with the 

absence of both MLG stabilizer extension 

springs. The loss of the locking mechanism 

could result in the collapse of the main 

landing gear. 

* * * * * 

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. 

Actions 

(g) Within 30 days after the effective date 

of this AD, revise the maintenance program 

by incorporating Task 320100–213 as 

specified in Bombardier Temporary Revision 

MRB–45, dated October 6, 2009, to Section 

1–32, Systems/Powerplant Maintenance 

Program, of Part 1 of the Maintenance Review 

Board Report of the Bombardier Q400 Dash 

8 Maintenance Requirements Manual, PSM 

1–84–7. The initial compliance time for Task 

320100–213 is within 600 flight hours after 

the effective date of this AD. 

No Alternative Actions or Intervals 

(h) After accomplishing the revision 

required by paragraph (g) of this AD, no 

alternative actions (e.g., inspections) or 

intervals may be used unless the actions or 

intervals are approved as an alternative 

method of compliance (AMOC) in 

accordance with the procedures specified in 

paragraph (i) 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, 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. 

Related Information 

(j) Refer to MCAI Transport Canada Civil 

Aviation (TCCA) Airworthiness Directive 

CF–2010–22, dated July 20, 2010; and 

Bombardier Temporary Revision MRB–45, 

dated October 6, 2009, to Section 

1–32, Systems/Powerplant Maintenance 

Program, of Part 1 of the Maintenance Review 

Board Report of the Bombardier Q400 Dash 

8 Maintenance Requirements Manual, PSM 

1–84–7; for related information. 

Issued in Renton, Washington, on April 12, 

2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–9408 Filed 4–18–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0312; Directorate 

Identifier 2010–NM–159–AD] 

RIN 2120–AA64 

Airworthiness Directives; Empresa 

Brasileira de Aeronautica S.A. 

(EMBRAER) Model EMB–135ER, 

–135KE, –135KL, and –135LR 

Airplanes; and Model EMB–145, 

–145ER, –145MR, –145LR, –145MP, and 

–145EP Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above. 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: 

This [Brazilian] AD results from reports of 

cracking in the firewall of the auxiliary 

power unit (APU). This AD is being issued 

to detect and correct this cracking, which 

could result in reduced structural integrity of 

the fuselage and empennage in the event that 


jdjones on DSK8KYBLC1PROD with PROPOSALS-1