68688 Federal Register / Vol. 75, No. 216 / Tuesday, November 9, 2010 / Rules and Regulations 

Restatement of Requirements of AD 2004– 

23–11, With Revised Service Information 

Inspection 

(g) For all airplanes except Model DC–9– 

15F airplanes, at the later of the times 

specified in paragraphs (g)(1) and (g)(2) of 

this AD: Do a high frequency eddy current 

inspection to detect cracks in the vertical 

radius of the upper cap of the center wing 

rear spar, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin DC9–57–223, dated July 21, 

2003; or Revision 1, dated August 13, 2009. 

After the effective date of this AD, only 

Revision 1 may be used. 

(1) Before the accumulation of 25,000 total 

flight cycles. 

(2) Within 15,000 flight cycles or 5 years 

after December 20, 2004 (the effective date of 

AD 2004–23–11), whichever occurs first. 

Corrective Action 

(h)(1) If no crack is found during any 

inspection required by paragraph (g) of this 

AD, then repeat the inspection thereafter at 

intervals not to exceed 15,000 flight cycles or 

5 years, whichever occurs first, until the 

initial inspection required by paragraph (i) of 

this AD is done. 

(2) If any crack is found during the 

inspection required by paragraph (g) of this 

AD, before further flight, repair per a method 

approved by the Manager, Los Angeles 

Aircraft Certification Office (ACO), FAA. For 

a repair method to be approved by the 

Manager, Los Angeles ACO, as required by 

this paragraph, the Manager’s approval letter 

must specifically refer to this AD. 

New Requirements of This AD 

Inspection 

(i) At the later of the times specified in 

paragraphs (i)(1) and (i)(2) of this AD: Do a 

high frequency eddy current inspection to 

detect cracking in the vertical leg (also 

known as the ‘‘vertical radius’’) and 

horizontal flange of the left and right rear 

spar upper cap, inboard and outboard sides, 

at the bulkhead at wing station Xcw=58.500, 

in accordance with the Accomplishment 

Instructions of Boeing Service Bulletin DC9– 

57–223, Revision 1, dated August 13, 2009. 

If no cracking is found, repeat the inspection 

thereafter at intervals not to exceed 15,000 

flight cycles or 5 years, whichever occurs 

first. Accomplishment of the initial 

inspection required by paragraph (i) of this 

AD terminates the requirements of 

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

(1) Before the accumulation of 25,000 total 

flight cycles. 

(2) Within 15,000 flight cycles or 5 years 

after accomplishing the most recent high 

frequency eddy current inspection required 

by paragraph (g) of this AD, whichever 

occurs first. 

Corrective Action 

(j) If any cracking is found during any 

inspection required by paragraph (i) of this 

AD, before further flight, repair the cracking 

using a method approved in accordance with 

the procedures specified in paragraph (k) of 

this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(k)(1) The Manager, Los Angeles ACO, 

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: Wahib Mina, Aerospace Engineer, 

Airframe Branch, ANM–120L, Los Angeles 

ACO, FAA, 3960 Paramount Boulevard, 

Lakewood, California 90712–4137; telephone 

(562) 627–5324; fax (562) 627–5210. 

(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. 

(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, Los Angeles 

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. 

(4) AMOCs approved previously in 

accordance with AD 2004–23–11, 

Amendment 39–13866, are approved as 

AMOCs for the corresponding provisions of 

paragraph (h)(2) of this AD. 

Material Incorporated by Reference 

(l) You must use Boeing Service Bulletin 

DC9–57–223, Revision 1, dated August 13, 

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, 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. 

(3) You may review copies of the service 

information at the FAA, 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 October 

21, 2010. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–28084 Filed 11–8–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0483; Directorate 

Identifier 2010–NM–065–AD; Amendment 

39–16502; AD 2010–23–13] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 757 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Model 757 airplanes. This AD requires 

changing the lower fixed leading edge 

panel assemblies immediately outboard 

of the nacelles at slats 4 and 7. This AD 

results from reports of Model 757 

airplanes in service that have drain 

holes and unsealed panel assemblies in 

the fixed leading edge adjacent to the 

inboard end of slats 4 and 7 that are too 

close to the hot portion of the engines. 

We are issuing this AD to prevent fuel 

leaking onto an engine and a consequent 

fire. 

DATES: This AD is effective December 

14, 2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of December 14, 2010. 

ADDRESSES: 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. 

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) 


wwoods2 on DSK1DXX6B1PROD with RULES_PART 1
Federal Register / Vol. 75, No. 216 / Tuesday, November 9, 2010 / Rules and Regulations 68689 

is the Document Management Facility, 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Tak Kobayashi, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 917–6499; fax (425) 917–6590. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an airworthiness 

directive (AD) that would apply to all 

Model 757 airplanes. That NPRM was 

published in the Federal Register on 

June 3, 2010 (75 FR 31329). That NPRM 

proposed to require changing the lower 

fixed leading edge panel assemblies 

immediately outboard of the nacelles at 

slats 4 and 7. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comments received from 

the commenters. 

Support for Proposed AD 

Boeing concurred with the contents of 

the proposed AD. FedEx, Continental 

Airlines, and American Airlines had no 

technical objection to changing the 

lower fixed leading edge panel 

assemblies immediately outboard of the 

nacelles at slats 4 and 7, as specified in 

the proposed AD. 

Request To Correct Part Number of 

Washer 

FedEx, Continental Airlines, and 

American Airlines requested that we 

correct the part number of a washer 

used in Figures 1 and 4 of Boeing 

Special Attention Service Bulletin 757– 

57–0070, dated January 27, 2010. The 

commenters stated that Boeing Service 

Bulletin Information Notice 757–57– 

0070 IN 01, dated March 17, 2010, 

corrects the part number of the washer, 

and that by including this correct part 

number in the proposed AD, requests 

for alternative methods of compliance 

(AMOC) will be reduced. 

We agree with the request as stated. 

We have added the correct part number 

to paragraph (g) of this AD. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

with the change described previously. 

We also determined that this change 

will not increase the economic burden 

on any operator or increase the scope of 

the AD. 

Costs of Compliance 

We estimate that this AD affects 697 

airplanes of U.S. registry. We also 

estimate that it takes 9 work-hours per 

product to comply with this AD. The 

average labor rate is $85 per work-hour. 

Based on these figures, we estimate the 

cost of this AD to the U.S. operators to 

be $533,205, or $765 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 

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 

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. 

You can find our regulatory 

evaluation and the estimated costs of 

compliance 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 airworthiness 

directive (AD): 

2010–23–13 The Boeing Company: 

Amendment 39–16502. Docket No. 

FAA–2010–0483; Directorate Identifier 

2010–NM–065–AD. 

Effective Date 

(a) This AD is effective December 14, 2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to all The Boeing 

Company Model 757–200, –200PF, –200CB, 

and –300 series airplanes, certificated in any 

category. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 57: Wings. 

Unsafe Condition 

(e) This AD results from reports of Model 

757 airplanes in service that have drain holes 

and unsealed panel assemblies in the fixed 

leading edge adjacent to the inboard end of 

slats 4 and 7 that are too close to the hot 

portion of the engines. The Federal Aviation 

Administration is issuing this AD to prevent 

fuel leaking onto an engine and a consequent 

fire. 

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. 

Action 

(g) Within 60 months after the effective 

date of this AD, change the lower fixed 

leading edge panel assemblies immediately 

outboard of the nacelles at slats 4 and 7, in 

accordance with the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 757–57–0070, dated January 

27, 2010; except, where the service bulletin 

specifies washer part number (P/N) 

NAS11490632J for the modification of the 

lower fixed leading edge panel assemblies, 

this AD requires installation of P/N 

NAS1149D0632J. 


wwoods2 on DSK1DXX6B1PROD with RULES_PART 1
68690 Federal Register / Vol. 75, No. 216 / Tuesday, November 9, 2010 / Rules and Regulations 

Alternative Methods of Compliance 

(AMOCs) 

(h)(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. Send information to ATTN: Tak 

Kobayashi, Aerospace Engineer, Propulsion 

Branch, ANM–140S, FAA, Seattle Aircraft 

Certification Office, 1601 Lind Avenue, SW., 

Renton, Washington 98057–3356; telephone 

(425) 917–6499; fax (425) 917–6590. 

Information may be e-mailed to: 9-ANMSeattle-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 reference this AD. 

Material Incorporated by Reference 

(i) You must use Boeing Special Attention 

Service Bulletin 757–57–0070, dated January 

27, 2010, 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 October 

23, 2010. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–28160 Filed 11–8–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0548; Directorate 

Identifier 2010–NM–041–AD; Amendment 

39–16497; AD 2010–23–08] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Model BD–700–1A10 and BD–700– 

1A11 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: 

Following five reported cases of balance 

washer screw failure on similar RATs [ram 

air turbines]/air driven generators installed 

on other aircraft types, an investigation 

* * * determined that a specific batch of the 

screws had a metallographic non-conformity 

that increased their susceptibility to brittle 

fracture. * * * 

Failure of a balance washer screw can 

result in loss of the related balance washer, 

with consequent turbine imbalance. Such 

imbalance could potentially result in RAT 

structural failure (including blade failure), 

loss of RAT electrical power and structural 

damage to the aircraft and, if deployment was 

activated by a dual engine shutdown, could 

also result in loss of hydraulic power for the 

flight controls [and consequent reduced 

ability of the flightcrew to maintain the safe 

flight and landing of the airplane]. 

* * * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

December 14, 2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of December 14, 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: 

Christopher Alfano, 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– 

7340; 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 June 4, 2010 (75 FR 31731). 

That NPRM proposed to correct an 

unsafe condition for the specified 

products. The MCAI states: 

Following five reported cases of balance 

washer screw failure on similar RATs [ram 

air turbine]/air driven generators installed on 

other aircraft types, an investigation by 

Hamilton Sundstrand determined that a 

specific batch of the screws had a 

metallographic non-conformity that 

increased their susceptibility to brittle 

fracture. Subsequently, it was established 

that 187 RATs [Part Number (P/N) GL456– 

1101–7 and Hamilton Sundstrand P/Ns in the 

762826 series] had non-conforming screws 

installed either during production or possibly 

during maintenance or repair at Hamilton 

Sundstrand repair stations. 

Failure of a balance washer screw can 

result in loss of the related balance washer, 

with consequent turbine imbalance. Such 

imbalance could potentially result in RAT 

structural failure (including blade failure), 

loss of RAT electrical power and structural 

damage to the aircraft and, if deployment was 

activated by a dual engine shutdown, could 

also result in loss of hydraulic power for the 

flight controls [and consequent reduced 

ability of the flightcrew to maintain the safe 

flight and landing of the airplane]. 

This [Canadian] directive mandates 

checking of the RAT and replacing the 

balance washer screws, if required. It also 

prohibits future installation of unmodified 

RATs. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Actions Since NPRM Was Issued 

We have determined that this AD 

should refer to the latest service 

information. We have reviewed 

Bombardier Service Bulletin 700–1A11– 

24–014, Revision 02, dated March 15, 

2010; and Bombardier Service Bulletin 

700–24–075, Revision 02, dated March 

15, 2010; which introduce minor 

changes, but do not add any additional 

work. We have revised this final rule to 

include the latest version of the 

applicable Bombardier service 

information and to provide credit for 

work done before the effective date of 

this AD, in accordance with the 

previous revisions of the service 

information. 


wwoods2 on DSK1DXX6B1PROD with RULES_PART 1