38064 Federal Register / Vol. 75, No. 126 / Thursday, July 1, 2010 / Proposed Rules 

Issued in Renton, Washington, on June 23, 

2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–15982 Filed 6–30–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0643; Directorate 

Identifier 2010–NM–030–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Model DHC–8 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: 

The landing gear alternate extension 

system in the cockpit is accessible through an 

access panel located on the cockpit floor. 

There have been reports of failure of the 

access panel latch assembly as a consequence 

of repeated closure of the access panel 

involving the use of excessive force. Failure 

of the latch assembly can result in the access 

panel being jammed in the closed position, 

and require mechanical prying to open. 

An undetected or uncorrected latch failure 

condition in the access panel can prevent 

immediate access to the landing gear 

alternate extension system by the flight crew 

during an emergency. * * * 

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 August 16, 2010. 

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., 400 Coˆte-Vertu Road West, Dorval, 

Que ́bec H4S 1Y9, Canada; telephone 

514–855–5000; fax 514–855–7401; 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: 

Craig Yates, Aerospace Engineer, 

Airframe and Mechanical Systems 

Branch, ANE–171, New York Aircraft 

Certification Office, FAA, 1600 Stewart 

Avenue, Suite 410, Westbury, New York 

11590; telephone (516) 228–7355; 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–2010–0643; Directorate Identifier 

2010–NM–030–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 have lengthened the 30-day 

comment period for proposed ADs that 

address MCAI originated by aviation 

authorities of other countries to provide 

adequate time for interested parties to 

submit comments. The comment period 

for these proposed ADs is now typically 

45 days, which is consistent with the 

comment period for domestic transport 

ADs. 

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 

The Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2009–46, 

dated December 14, 2009 (referred to 

after this as ‘‘the MCAI’’), to correct an 

unsafe condition for the specified 

products. The MCAI states: 

The landing gear alternate extension 

system in the cockpit is accessible through an 

access panel located on the cockpit floor. 

There have been reports of failure of the 

access panel latch assembly as a consequence 

of repeated closure of the access panel 

involving the use of excessive force. Failure 

of the latch assembly can result in the access 

panel being jammed in the closed position, 

and require mechanical prying to open. 

An undetected or uncorrected latch failure 

condition in the access panel can prevent 

immediate access to the landing gear 

alternate extension system by the flight crew 

during an emergency. This Directive requires 

the replacement of the existing latch 

assembly with a stronger modified latch 

assembly. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Bombardier, Inc. has issued Service 

Bulletin 8–32–166, Revision A, dated 

January 29, 2009; and Service Bulletin 

84–32–57, Revision A, dated June 15, 

2009. 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. 

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Federal Register / Vol. 75, No. 126 / Thursday, July 1, 2010 / Proposed Rules 38065 

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 198 products of U.S. 

registry. We also estimate that it would 

take about 3 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 about $815 per 

product. Where the service information 

lists required parts costs that are 

covered under warranty, we have 

assumed that there will be no charge for 

these costs. As we do not control 

warranty coverage for affected parties, 

some parties may incur costs higher 

than estimated here. Based on these 

figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$211,860, or $1,070 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–2010– 

0643; Directorate Identifier 2010–NM– 

030–AD. 

Comments Due Date 

(a) We must receive comments by August 

16, 2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to the airplanes 

identified in paragraphs (c)(1) and (c)(2) of 

this AD, certificated in any category. 

(1) Bombardier, Inc. Model DHC–8–101, 

–102, –103, –106, –201, –202, –301, –311, 

and –315 airplanes, serial numbers 003 

through 658 inclusive. 

(2) Bombardier, Inc. Model DHC–8–400, 

–401, –402 airplanes, serial numbers 4001, 

4003, 4004, 4006, and 4008 through 4187 

inclusive. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 32: Landing gear. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

The landing gear alternate extension 

system in the cockpit is accessible through an 

access panel located on the cockpit floor. 

There have been reports of failure of the 

access panel latch assembly as a consequence 

of repeated closure of the access panel 

involving the use of excessive force. Failure 

of the latch assembly can result in the access 

panel being jammed in the closed position, 

and require mechanical prying to open. 

An undetected or uncorrected latch failure 

condition in the access panel can prevent 

immediate access to the landing gear 

alternate extension system by the flight crew 

during an emergency. * * * 

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 6,000 flight hours or 36 months 

after the effective date of this AD, whichever 

comes first: Replace the latch assembly of the 

access panel for the alternate extension 

system for the landing gear with a modified 

latch assembly, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 8–32–166, Revision A, dated 

January 29, 2009 (for Model DHC–8–100, 

DHC–8–200, and DHC–8–300 series 

airplanes); or Bombardier Service Bulletin 

84–32–57, Revision A, dated June 15, 2009 

(for Model DHC–8–400 series airplanes). 

Actions Accomplished According to 

Previous Issue of Service Bulletin 

(h) Actions accomplished before the 

effective date of this AD according to 

Bombardier Service Bulletin 8–32–166, dated 

April 14, 2008; or Bombardier Service 

Bulletin 84–32–57, dated April 30, 2008; as 

applicable; are considered acceptable for 

compliance with the corresponding actions 

specified in 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 Aircraft 

Certification Office, ANE–170, FAA, has the 

authority to approve 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 

on any airplane to which the AMOC applies, 

notify your principal maintenance inspector 

WReier-Aviles on DSKGBLS3C1PROD with PROPOSALS

38066 Federal Register / Vol. 75, No. 126 / Thursday, July 1, 2010 / Proposed Rules 

(PMI) or principal avionics inspector (PAI), 

as appropriate, or lacking a principal 

inspector, your local Flight Standards 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. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, under the 

provisions of the Paperwork Reduction Act 

(44 U.S.C. 3501 et seq.), the Office of 

Management and Budget (OMB) has 

approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(j) Refer to MCAI Canadian Airworthiness 

Directive CF–2009–46, dated December 14, 

2009; Bombardier Service Bulletin 8–32–166, 

Revision A, dated January 29, 2009; and 

Bombardier Service Bulletin 84–32–57, 

Revision A, dated June 15, 2009; for related 

information. 

Issued in Renton, Washington, on June 23, 

2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–15983 Filed 6–30–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0646; Directorate 

Identifier 2009–NM–223–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 727, 727C, 727–100, 

727–100C, 727–200, and 727–200F 

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 all 

Model 727, 727C, 727–100, 727–100C, 

727–200, and 727–200F series airplanes. 

This proposed AD would require 

repetitive detailed inspections of the aft 

pressure bulkhead web for cracking, and 

repair if necessary. For certain 

airplanes, this proposed AD also would 

provide for an optional preventative 

modification of the aft pressure 

bulkhead web, which would terminate 

certain repetitive detailed inspections. 

This proposed AD results from reports 

of cracks in the aft pressure bulkhead 

web. We are proposing this AD to detect 

and correct cracking in the aft pressure 

bulkhead web, which could adversely 

affect the structural integrity of the 

airplane, resulting in difficulty 

maintaining cabin pressurization or 

rapid decompression of the airplane. 

DATES: We must receive comments on 

this proposed AD by August 16, 2010. 

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; e-mail 

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: 

Berhane Alazar, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 917–6577; fax (425) 917–6590. 

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–2010–0646; Directorate Identifier 

2009–NM–223–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 13 reports of cracks 

in the aft pressure bulkhead web 

ranging from 0.75 inch to 11.8 inches in 

length at the buttock line 61, between 

water line (WL) 220 and WL 228. The 

cracks originated at the hydraulic line 

support brackets, which were installed 

in production after airplane line number 

1136, or in accordance with Boeing 

Service Bulletin 727–29–0057. The 

cracks were found in airplanes that had 

accumulated between 14,939 total flight 

hours and 39,369 total flight hours, and 

between 10,685 total flight cycles and 

29,357 total flight cycles. The cracking 

is attributed to fatigue of the aft pressure 

bulkhead web due to vibrations from the 

number 1 engine hydraulic pump line, 

in addition to normal pressurization 

cycles. Material analysis revealed 

multiple crack initiation sites and no 

evidence of corrosion. This condition, if 

not corrected, could result in difficulty 

maintaining cabin pressurization or 

rapid decompression of the airplane. 

Relevant Service Information 

We have reviewed Boeing Special 

Attention Service Bulletin 727–53– 

0232, dated September 23, 2009. This 

service bulletin describes procedures for 

initial and repetitive detailed 

inspections of the aft pressure bulkhead 

web for any cracking around the 

hydraulic line support bracket, and 

repair of any crack found. For certain 

airplanes, this service bulletin describes 

procedures for installing an optional 

preventative modification if no cracking 

is found during the detailed inspections. 

The preventative modification includes 

doing high frequency eddy current 

WReier-Aviles on DSKGBLS3C1PROD with PROPOSALS