Federal Register / Vol. 75, No. 194 / Thursday, October 7, 2010 / Rules and Regulations 61987 

defective. We are issuing this AD to prevent 

failure of this equipment, which could 

jeopardize flight safety. 

Compliance 

(f) Comply with this AD within the 

compliance times specified, unless already 

done. 

Door Equipment Installation 

(g) Within 30 days after the effective date 

of this AD, install certain equipment 

associated with the flight deck door, in 

accordance with Boeing Service Bulletin 

747–52–2293, dated September 4, 2009. 

Alternative Methods of Compliance 

(AMOCs) 

(h)(1) The Manager, Seattle Aircraft 

Certification Office, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

Send information to Robert Kaufman, 

Aerospace Engineer, Cabin Safety and 

Environmental Systems Branch, ANM–150S, 

FAA, Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 917–6433; fax 

(425) 917–6590. Or e-mail information to 9- 

ANM-Seattle-ACO-AMOC-Requests@faa.gov. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your principal maintenance inspector 

(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 refer to this AD. 

Incorporation by Reference 

(i) You must use Boeing Service Bulletin 

747–52–2293, dated September 4, 2009, to do 

the actions required by this AD, unless the 

AD specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(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; e-mail 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 NARA, 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 

September 23, 2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–25194 Filed 10–6–10; 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; Amendment 

39–16462; AD 2010–21–02] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Model DHC–8 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This 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. * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

November 12, 2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of November 12, 2010. 

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: 

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: 

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 July 1, 2010 (75 FR 38064). 

That NPRM proposed 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. issued Service 

Bulletin 8–32–166, Revision B, dated 

March 2, 2010. We cited Bombardier 

Service Bulletin 8–32–166, Revision A, 

dated January 29, 2009, in the NPRM. 

Bombardier Service Bulletin 8–32–166, 

Revision B, dated March 2, 2010, 

updates the References section and adds 

a Note to the Accomplishment 

Instructions section. We have changed 

paragraph (g) of this AD to specify 

Revision B of that service bulletin, and 

added Bombardier Service Bulletin 8– 

32–166, Revision A, dated January 29, 

2009, to paragraph (h) of this AD. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comments received. Air 

Line Pilots Association, International, 

supports the NPRM. Hawaii Island Air, 

Piedmont Airlines, and Mesa Airlines 

request that we revise the NPRM to refer 

to Bombardier Service Bulletin 8–32– 

166, Revision B, dated March 2, 2010, 

as described previously. 


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61988 Federal Register / Vol. 75, No. 194 / Thursday, October 7, 2010 / Rules and Regulations 

Conclusion 

We reviewed the available data, 

including the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously. 

We determined that these changes will 

not increase the economic burden on 

any operator or increase the scope of the 

AD. 

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 required different 

actions in this AD from those in the 

MCAI in order to follow our FAA 

policies. Any such differences are 

highlighted in a NOTE within the AD. 

Costs of Compliance 

We estimate that this AD will affect 

about 198 products of U.S. registry. We 

also estimate that it will take about 3 

work-hours per product to comply with 

the basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Required parts will 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 parts. 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 this AD 

to the 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 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 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); 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 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, 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: 

2010–21–02 Bombardier, Inc.: Amendment 

39–16462. Docket No. FAA–2010–0643; 

Directorate Identifier 2010–NM–030–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective November 12, 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 B, dated 

March 2, 2010 (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). 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(h) Actions accomplished before the 

effective date of this AD in accordance with 

the service information identified in Table 1 

of this AD are considered acceptable for 

compliance with the corresponding actions 

specified in this AD. 


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Federal Register / Vol. 75, No. 194 / Thursday, October 7, 2010 / Rules and Regulations 61989 

TABLE 1—PREVIOUS SERVICE INFORMATION

Bombardier Service Bulletin— Revision— Dated— 

8–32–166 ............................................................................................................................................. Original .................... April 14, 2008. 

8–32–166 ............................................................................................................................................. A .............................. January 29, 2009. 

84–32–57 ............................................................................................................................................. Original .................... April 30, 2008. 

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 

(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 B, dated March 2, 2010; and 

Bombardier Service Bulletin 84–32–57, 

Revision A, dated June 15, 2009; for related 

information. 

Material Incorporated by Reference 

(k) You must use Bombardier Service 

Bulletin 84–32–57, Revision A, dated June 

15, 2009; or Bombardier Service Bulletin 8– 

32–166, Revision B, dated March 2, 2010; as 

applicable; to do the actions required by this 

AD, unless the AD specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Bombardier, Inc., 400 CoˆteVertu Road West, Dorval, Que ́bec H4S 1Y9, 

Canada; telephone 514–855–5000; fax 514– 

855–7401; e-mail 

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 NARA, 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 

September 23, 2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–25016 Filed 10–6–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0639; Directorate 

Identifier 2009–NM–232–AD; Amendment 

39–16463; AD 2010–21–03] 

RIN 2120–AA64 

Airworthiness Directives; McDonnell 

Douglas Corporation Model DC–8–31, 

DC–8–32, DC–8–33, DC–8–41, DC–8– 

42, and DC–8–43 Airplanes; Model DC– 

8–50 Series Airplanes; Model DC–8F– 

54 and DC–8F–55 Airplanes; Model 

DC–8–60 Series Airplanes; Model DC– 

8–60F Series Airplanes; Model DC–8– 

70 Series Airplanes; and Model DC–8– 

70F Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD) 

that applies to all of the McDonnell 

Douglas Corporation airplanes 

identified above. The existing AD 

currently requires revising the 

maintenance program to incorporate 

new airworthiness limitations for fuel 

tank systems to satisfy Special Federal 

Aviation Regulation No. 88 

requirements. This new AD adds 

requirements to revise the maintenance 

program to incorporate specific Critical 

Design Configuration Control 

Limitations (CDCCL) information and 

install fuel tank float switch in-line 

fuses. This new AD also adds two 

Airworthiness Limitations inspections 

(ALIs). This AD results from a design 

review of the fuel tank systems. We are 

issuing this AD to prevent the potential 

for ignition sources inside fuel tanks 

caused by latent failures, alterations, 

repairs, or maintenance actions, which, 

in combination with flammable fuel 

vapors, could result in a fuel tank 

explosion and consequent loss of the 

airplane. 

DATES: This AD becomes effective 

November 12, 2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of November 12, 2010. 

On May 27, 2008 (73 FR 21523, April 

22, 2008), the Director of the Federal 

Register approved the incorporation by 

reference of a certain other publication 

listed in the AD. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, 3855 

Lakewood Boulevard, MC D800–0019, 

Long Beach, California 90846–0001; 

telephone 206–544–5000, extension 2; 

fax 206–766–5683; e-mail 

dse.boecom@boeing.com; Internet 

https://www.myboeingfleet.com. 

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 address for the 

Docket Office (telephone 800–647–5527) 

is the Document Management Facility, 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 


srobinson on DSKHWCL6B1PROD with RULES