61982 Federal Register / Vol. 75, No. 194 / Thursday, October 7, 2010 / Rules and Regulations 

your model helicopter, or visually inspect the 

MGB planet gear carrier in accordance with 

the Operational Procedure, paragraphs 2.B.3. 

through paragraph 2.B.3.a.1, of the EASB 

applicable to your model helicopter. Each 

EASB at the stated revision level is dated 

November 16, 2009. 

(b) If a crack is found in the planet gear 

carrier, replace the MGB with an airworthy 

MGB before further flight. 

(c) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Contact the Manager, Safety 

Management Group, FAA, Attn: Gary Roach, 

Aviation Safety Engineer, Rotorcraft 

Directorate, FAA, 2601 Meacham Blvd., Fort 

Worth, Texas 76137, telephone (817) 222– 

5130, fax (817) 222–5961, for information 

about previously approved alternative 

methods of compliance. 

(d) The Joint Aircraft System/Component 

(JASC) Code is 6320: Main Rotor Gearbox. 

(e) The inspections shall be done in 

accordance with the specified portions of 

Eurocopter Emergency Alert Service Bulletin 

No. 05A007, Revision 2, No. 05.00.48, 

Revision 3, No. 05.26, Revision 2, or No. 

05.33, Revision 2. Each service bulletin at the 

stated revision level is dated November 16, 

2009. The Director of the Federal Register 

approved this incorporation by reference in 

accordance with 5 U.S.C. 552(a) and 1 CFR 

part 51. Copies may be obtained from 

American Eurocopter Corporation, 2701 

Forum Drive, Grand Prairie, Texas 75053– 

4005, telephone (972) 641–3460, fax (972) 

641–3527. Copies may be inspected at the 

FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham Blvd., 

Room 663, Fort Worth, Texas, or 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. 

(f) This amendment becomes effective on 

November 12, 2010. 

Note: The subject of this AD is addressed 

in European Aviation Safety Agency AD No. 

2007–0288–E, dated November 15, 2007. 

Issued in Fort Worth, Texas, on September 

22, 2010. 

Mark R. Schilling, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–24725 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–2010–0474; Directorate 

Identifier 2009–NM–056–AD; Amendment 

39–16465; AD 2010–21–05] 

RIN 2120–AA64 

Airworthiness Directives; BAE 

Systems (Operations) Limited Model 

4101 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing 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: 

During ground manoeuvring, prolonged 

operation with either engine in the restricted 

range between 82% and 90% RPM 

[revolutions per minute] will result in 

damage [e.g., cracking of the blade or hub] to 

the propeller assembly that could eventually 

result in the release of a propeller blade. 

* * * EASA [European Aviation Safety 

Agency] AD 2007–0268 [which corresponds 

to FAA AD 2008–13–02, amendment 39– 

15565] was issued to require the installation 

of a Propeller Warning Placard and 

implementation of a corresponding Aircraft 

Flight Manual (AFM) limitation instructing 

the flight crew to taxi with the condition 

lever at FLIGHT in order to minimise the 

time spent by the engines in the restricted 

range. BAE Systems has now developed a 

Propeller Speed Warning System * * *. 

* * * * * 

A released propeller blade could 

result in engine failure and loss of 

control of the airplane. 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 a certain publication listed in this AD 

as of November 12, 2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of July 24, 2008 (73 FR 

34847, June 19, 2008). 

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: 

Todd Thompson, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1175; fax (425) 227–1149. 

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 May 10, 2010 (75 FR 25785), 

and proposed to supersede AD 2008– 

13–02, amendment 39–15565 (73 FR 

34847), June 19, 2008. That NPRM 

proposed to correct an unsafe condition 

for the specified products. 

Since we issued AD 2008–13–02, 

inadvertent high RPMs taxiing 

operations have been reported to have 

caused stress to the propeller blades, 

which can result in dangerous blade 

cracks. The European Aviation Safety 

Agency (EASA), which is the Technical 

Agent for the Member States of the 

European Community, has issued EASA 

Airworthiness Directive 2009–0038, 

dated February 18, 2009 (referred to 

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

unsafe condition for the specified 

products. The MCAI states: 

During ground manoeuvring, prolonged 

operation with either engine in the restricted 

range between 82% and 90% RPM 

[revolutions per minute] will result in 

damage [e.g., cracking of the blade or hub] to 

the propeller assembly that could eventually 

result in the release of a propeller blade. 

To correct this unsafe condition, EASA AD 

2007–0268 [which corresponds to FAA AD 

2008–13–02, amendment 39–15565] was 

issued to require the installation of a 

Propeller Warning Placard and 

implementation of a corresponding Aircraft 

Flight Manual (AFM) limitation, instructing 

the flight crew to taxi with the condition 

lever at FLIGHT in order to minimise the 

time spent by the engines in the restricted 

range. BAE Systems has now developed a 

Propeller Speed Warning System, the 

embodiment of which will allow taxiing with 

the condition lever at TAXI, through the 

introduction of a revised Flight Manual 

Limitation. 

For the reasons described above, this EASA 

AD retains the requirements of EASA AD 

2007–0268, which is superseded, and 

requires the installation of a Propeller Speed 

Warning System. 

A released propeller blade could 

result in engine failure and loss of 

control of the airplane. You may obtain 


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further information by examining the 

MCAI in the AD docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Clarification of Paragraph (h)(2) of This 

AD 

The revision to the BAE Jetstream 

Series 4100 Flight Manual (FM) 

includes information on introducing a 

propeller speed warning system on 

airplanes that have Modification 

JM41674. We have also removed the 

reference to the alternative methods of 

compliance (AMOC) paragraph and 

have specified the appropriate source of 

approval procedures to accomplish the 

requirements of paragraph (h)(2) of this 

AD. 

Conclusion 

We reviewed the available data 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 3 products of U.S. registry. 

The actions that are required by AD 

2008–13–02 and retained in this AD 

take about 2 work-hours per product, at 

an average labor rate of $85 per workhour. Required parts cost about $25 per 

product. Based on these figures, the 

estimated cost of the currently required 

actions is $195 per product. 

We estimate that it will take about 20 

work-hours per product to comply with 

the new basic requirements of this AD. 

The average labor rate is $85 per workhour. Required parts will cost about 

$2,800 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 

this AD to the U.S. operators to be 

$14,085, or $4,695 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 

removing amendment 39–15565 (73 FR 

34847, June 19, 2008) and adding the 

following new AD: 

2010–21–05 BAE Systems (Operations) 

Limited: Amendment 39–16465. Docket 

No. FAA–2010–0474; Directorate 

Identifier 2009–NM–056–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective November 12, 2010. 

Affected ADs 

(b) This AD supersedes AD 2008–13–02, 

amendment 39–15565. 

Applicability 

(c) This AD applies to all BAE SYSTEMS 

(Operations) Limited Model 4101 airplanes, 

certificated in any category. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 61: Propellers/Propulsors. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

During ground manoeuvring, prolonged 

operation with either engine in the restricted 

range between 82% and 90% RPM 

[revolutions per minute] will result in 

damage [e.g., cracking of the blade or hub] to 

the propeller assembly that could eventually 

result in the release of a propeller blade. 

To correct this unsafe condition, EASA 

[European Aviation Safety Agency] AD 2007– 

0268 [which corresponds to FAA AD 2008– 

13–02, amendment 39–15565] was issued to 

require the installation of a Propeller 

Warning Placard and implementation of a 

corresponding Aircraft Flight Manual (AFM) 

limitation, instructing the flight crew to taxi 


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61984 Federal Register / Vol. 75, No. 194 / Thursday, October 7, 2010 / Rules and Regulations 

with the condition lever at FLIGHT in order 

to minimise the time spent by the engines in 

the restricted range. BAE Systems has now 

developed a Propeller Speed Warning 

System, embodiment of which will allow 

taxiing with the condition lever at TAXI, 

through the introduction of a revised Flight 

Manual Limitation. 

For the reasons described above, this EASA 

AD retains the requirements of EASA AD 

2007–0268, which is superseded, and 

requires the installation of a Propeller Speed 

Warning System. 

A released propeller blade could result in 

engine failure and 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. 

Restatement of Requirements of AD–2008– 

13–02 

Actions 

(g) Within 90 days after July 24, 2008 (the 

effective date of AD 2008–13–02), unless 

already done, do the following actions. 

(1) Replace the existing Propeller 

Limitations Placard in the cockpit with a new 

placard, in accordance with the 

Accomplishment Instructions of BAE 

Systems (Operations) Limited Service 

Bulletin J41–11–027, dated March 29, 2007. 

(2) Revise the BAE Jetstream Series 4100 

Flight Manual (FM) to include the 

information in BAE Jetstream Series 4100 

General Amendment G12, approved January 

2007; and BAE Jetstream Series 4100 

Advance Amendment Bulletin 13, approved 

April 4, 2007. General Amendment G12 

describes a rolling take-off technique and the 

reduced possibility of landing with ice 

contaminating the wings, and adds a Gross 

Height/Pressure Altitude Conversion Chart. 

Advance Amendment Bulletin 13 introduces 

procedures for placing the propeller 

condition levers in the Flight position during 

all ground maneuvering. Operate the airplane 

according to the procedures in General 

Amendment G12 and Advance Amendment 

Bulletin 13. 

Note 1: This may be done by inserting 

copies of General Amendment G12 and 

Advance Amendment Bulletin 13 into the 

FM. When General Amendment G12 and 

Advance Amendment Bulletin 13 have been 

included in general revisions of the FM, the 

general revisions may be inserted in the FM, 

provided the relevant information in the 

general revision is identical to that in General 

Amendment G12 and Advance Amendment 

Bulletin 13. 

New Requirements of This AD 

Actions 

(h) Unless already done, do the following 

actions. 

(1) Within 6 months after the effective date 

of this AD, install a Propeller Speed Warning 

System (Modification JM41674), in 

accordance with Section 2 of BAE Systems 

(Operations) Limited Aircraft Change 

Information Bulletin J41–61–014, Issue 7, 

dated August 17, 2009. Before further flight 

after modification, do the actions required in 

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

(i) Remove the placard that was installed 

as required by paragraph (g)(1) of this AD. 

(ii) Remove BAE Jetstream Series 4100 

Advance Amendment Bulletin 13, approved 

April 4, 2007, from the FM. 

(2) Within 6 months after the effective date 

of this AD, revise the BAE Jetstream Series 

4100 FM to include information on 

introducing a propeller speed warning 

system, on airplanes that have Modification 

JM41674, using a method approved by the 

Manager, International Branch, ANM 116, 

Transport Airplane Directorate, FAA, or 

EASA (or its delegated agent). 

Note 2: Guidance on revising the BAE 

Jetstream Series 4100 FM, as required by 

paragraph (h)(2) of this AD, can be found in 

BAE Jetstream Series 4100 Particular 

Amendment 111, approved December 2008. 

FAA AD Differences 

Note 3: 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, International 

Branch, ANM–116, Transport Airplane 

Directorate, 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: Todd Thompson, 

Aerospace Engineer, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

227–1175; fax (425) 227–1149. 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 European Aviation Safety 

Agency (EASA) Airworthiness Directive 

2009–0038, dated February 18, 2009; and the 

service information identified in Table 1 of 

this AD; for related information. 

TABLE 1—SERVICE INFORMATION

Service information Date 

BAE Jetstream Series 4100 Advance Amendment Bulletin 13 to the Jetstream Series 4100 Flight Manual ....................... April 4, 2007. 

BAE Jetstream Series 4100 General Amendment G12 to the Jetstream Series 4100 Flight Manual ................................... January 2007. 

BAE Systems (Operations) Limited Aircraft Change Information Bulletin J41–61–014, Section 2, Issue 7 .......................... August 17, 2009. 

BAE Systems (Operations) Limited Service Bulletin J41–11–027 .......................................................................................... March 29, 2007. 

Material Incorporated by Reference 

(k) You must use the service information 

contained in Table 2 of this AD to do the 

actions required by this AD, unless the AD 

specifies otherwise. 

TABLE 2—ALL MATERIAL INCORPORATED BY REFERENCE

Service information Date 

BAE Jetstream Series 4100 Advance Amendment Bulletin 13 to the Jetstream Series 4100 Flight Manual ....................... April 4, 2007. 

BAE Jetstream Series 4100 General Amendment G12 to the Jetstream Series 4100 Flight Manual ................................... January 2007. 

BAE Systems (Operations) Limited Aircraft Change Information Bulletin J41–61–014, Section 2, Issue 7 .......................... August 17, 2009. 


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TABLE 2—ALL MATERIAL INCORPORATED BY REFERENCE—Continued 

Service information Date 

BAE Systems (Operations) Limited Service Bulletin J41–11–027 .......................................................................................... March 29, 2007. 

BAE Systems (Operations) Limited Aircraft 

Change Information Bulletin J41–61–014, 

Section 2, Issue 7, contains the following 

effective pages: 

LIST OF EFFECTIVE PAGES

Page title/description Page 

number(s) 

Issue 

number 

Date shown on 

page(s) 

Section 2, Installer Instructions ............................................................................... 15–50 7 August 17, 2009. 

(Section 1 of this document (pages 1–14) is 

not included.) 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

BAE Systems (Operations) Limited Aircraft 

Change Information Bulletin J41–61–014, 

Section 2, Issue 7, dated August 17, 2009, 

under 5 U.S.C. 552(a) and 1 CFR part 51. 

(2) The Director of the Federal Register 

previously approved the incorporation by 

reference of the service information 

contained in Table 3 of this AD on July 24, 

2008 (73 FR 34847, June 19, 2008). 

TABLE 3—MATERIAL PREVIOUSLY INCORPORATED BY REFERENCE

Service information Date 

BAE Jetstream Series 4100 Advance Amendment Bulletin 13 to the Jetstream Series 4100 Flight Manual ....................... April 4, 2007. 

BAE Jetstream Series 4100 General Amendment G12 to the Jetstream Series 4100 Flight Manual ................................... January 2007. 

BAE Systems (Operations) Limited Service Bulletin J41–11–027 .......................................................................................... March 29, 2007. 

(3) For service information identified in 

this AD, contact BAE Systems (Operations) 

Limited, Customer Information Department, 

Prestwick International Airport, Ayrshire, 

KA9 2RW, Scotland, United Kingdom; 

telephone +44 1292 675207; fax +44 1292 

675704; e-mail 

RApublications@baesystems.com; Internet 

http://www.baesystems.com/Businesses/ 

RegionalAircraft/index.htm. 

(4) 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. 

(5) 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. 2010–25018 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–2010–0950; Directorate 

Identifier 2009–NM–194–AD; Amendment 

39–16460; AD 2009–19–06] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 747–100, 747–100B, 747–100B 

SUD, 747–200B, 747–200F, 747–300, 

747–400, 747–400D, 747SP, and 747SR 

Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: This document publishes in 

the Federal Register an amendment 

adopting airworthiness directive (AD) 

2009–19–06 that was sent previously by 

individual notices to the known U.S. 

owners and operators of affected 

airplanes identified above. This AD 

requires installing certain equipment on 

the flight deck door. This AD was 

prompted by reports that the current 

design of the flight deck door is 

defective. We are issuing this AD to 

prevent failure of this equipment, which 

could jeopardize flight safety. 

DATES: This AD becomes effective 

October 12, 2010 to all persons except 

those persons to whom it was made 

immediately effective by AD 2009–19– 

06, which contained the requirements of 

this amendment. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of October 12, 2010. 

We must receive comments on this 

AD by November 22, 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 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 


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