Federal Register / Vol. 74, No. 124 / Tuesday, June 30, 2009 / Rules and Regulations 31169 

2.B.1, Figure 3, and Figure 4 in Turbomeca 

S.A. MSB No. A292 72 0825, Version A, 

dated May 27, 2009, to do the repair. 

Repetitive Visual Inspections 

(g) If no oil leakage is found, repeat the 

visual inspection every four flight hours, or 

after the last flight of each day, whichever 

comes first. 

(h) The actions required by paragraph (g) 

of this AD may be performed by the owner/ 

operator holding at least a private pilot 

certificate, and must be entered into the 

aircraft records showing compliance with 

this AD in accordance with 14 CFR 43.9 and 

14 CFR 91.417(a)(2)(v). 

Optional Terminating Action 

(i) As optional terminating action to the 

repetitive visual inspections in paragraph (g) 

of this AD, repair the affected modules M05 

as specified in paragraph (f)(2) of this AD. 

Alternative Methods of Compliance 

(j) The Manager, Engine Certification 

Office, has the authority to approve 

alternative methods of compliance for this 

AD if requested using the procedures found 

in 14 CFR 39.19. 

Related Information 

(k) European Aviation Safety Agency 

emergency airworthiness directive 2009– 

0117–E, dated June 2, 2009, also addresses 

the subject of this AD. 

Contact Information 

(l) For further information, contact: James 

Lawrence, Aerospace Engineer, Engine 

Certification Office, FAA, Engine and 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; email: james.lawrence@faa.gov; telephone 

(781) 238–7176; fax (781) 238–7199, for more 

information about this AD. 

Material Incorporated by Reference 

(m) You must use Turbomeca S.A. MSB 

No. A292 72 0825, Version A, dated May 27, 

2009, to identify the serial numbers of 

modules M05 affected by this AD, and to 

perform the inspections and repairs required 

by this AD. The Director of the Federal 

Register approved the incorporation by 

reference of this service bulletin in 

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

part 51. You can get a copy from Turbomeca, 

40220 Tarnos, France; telephone (33) 05 59 

74 40 00, fax (33) 05 59 74 45 15. You may 

review copies at the FAA, New England 

Region, 12 New England Executive Park, 

Burlington, MA; 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/ 

cfr/ibr-locations.html. 

Issued in Burlington, Massachusetts, on 

June 22, 2009. 

Peter A. White, 

Assistant Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. E9–15277 Filed 6–29–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0556; Directorate 

Identifier 2009–NM–112–AD; Amendment 

39–15942; AD 2009–13–03] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 747–400 and –400F Series 

Airplanes Powered by Rolls-Royce 

RB211 Series Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Boeing Model 747–400 and –400F series 

airplanes. This AD requires modifying 

certain thrust reverser control system 

wiring to the flap control unit (FCU). 

This AD results from a report of 

automatic retraction of the leading edge 

flaps during takeoff due to indications 

transmitted to the FCU from the thrust 

reverser control system. We are issuing 

this AD to prevent automatic retraction 

of the leading edge flaps during takeoff, 

which could result in reduced climb 

performance and consequent collision 

with terrain and obstacles or forced 

landing of the airplane. 

DATES: This AD is effective July 6, 2009. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of July 6, 2009. 

We must receive comments on this 

AD by August 31, 2009. 

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 

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 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: 

Douglas Bryant, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 917–6505; fax (425) 917–6590. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We received a report of automatic 

retraction of the leading edge flaps 

during takeoff on a Boeing Model 747– 

400 airplane powered by Rolls-Royce 

RB211–524G/H engines. The automatic 

retraction was due to indications 

transmitted to the flap control unit 

(FCU) from the thrust reverser control 

system. In order to prevent 

impingement of efflux air from the 

thrust reversers during landing rollout, 

the FCU is designed to automatically 

retract the Group A leading edge flaps 

when a REV Amber signal is received 

from either both inboard or both 

outboard thrust reversers, and the 

airplane is on the ground. In this event, 

the first REV amber signal was received 

prior to V1 (takeoff decision speed). The 

second REV amber signal was received 

several seconds later, after takeoff 

decision speed. At that time, the FCU 

performed as designed and retracted the 

Group A leading edge flaps. At rotation 

the flight crew reported buffeting and 

stick shaker activation. After liftoff, a 

signal from the air/ground logic system 

caused the FCU to send a command to 

the Group A leading edge flaps to redeploy after a five-second time delay. 

Re-deployment of the flaps takes 

approximately ten to fifteen additional 

seconds; during re-deployment, the 

flightcrew again reported buffeting and 

momentary stick shaker activation. The 

airplane jettisoned fuel and was landed 

safely; all four of the thrust reversers 

deployed and stowed normally after 

landing. 

In addition, one operator reported 12 

single-engine REV indications during 


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31170 Federal Register / Vol. 74, No. 124 / Tuesday, June 30, 2009 / Rules and Regulations 

takeoff over the past three years, leading 

to seven rejected takeoffs. The incident 

described above was the first known 

simultaneous two-engine event. 

These conditions, if not corrected, 

could result in reduced climb 

performance during takeoff and 

consequent collision with terrain and 

obstacles or forced landing of the 

airplane. 

Relevant Service Information 

We reviewed Boeing Alert Service 

Bulletin 747–78A2181, dated June 8, 

2009. The service information describes 

procedures for modifying certain thrust 

reverser control system wiring to the 

FCU in the P414 and P415 panels. The 

modification includes re-routing and reterminating one wire for each engine, 

and replacing the wire if necessary. 

FAA’s Determination and Requirements 

of This AD 

No airplanes affected by this AD are 

on the U.S. Register. We are issuing this 

AD because we evaluated all the 

relevant information and determined 

the unsafe condition described 

previously is likely to exist or develop 

on other products of the same type 

design. This AD requires accomplishing 

the actions specified in the service 

information described previously, 

except as described under ‘‘Difference 

Between the AD and the Service 

Information.’’ 

Difference Between the AD and the 

Service Information 

Operators should note that Boeing 

Alert Service Bulletin 747–78A2181, 

dated June 8, 2009, recommends that 

the modification be completed within 

90 days (after the issue date of the 

service bulletin). This AD specifies a 

compliance time of 60 days. In 

developing this compliance time, we 

considered the manufacturer’s 

recommended 90-day compliance time 

(after June 8, 2009, which is the service 

bulletin issue date), a risk assessment of 

the unsafe condition, the scope of work 

required, and the number of affected 

airplanes, as well as the time normally 

required for the rulemaking process to 

be completed (approximately 30 days). 

In consideration of both of these factors, 

we find that a compliance time of 60 

days after the effective date of this AD 

will fall approximately at the same time 

(calendar date) as the compliance time 

recommended by the manufacturer, and 

represents an appropriate interval of 

time for affected airplanes to continue to 

operate without compromising safety. 

By adjusting the compliance time 

interval in this way: 

1. Operators will get a full 60 days in 

which to complete the modification; 

and 

2. The modification can be done 

within an interval of time that parallels 

normal scheduled maintenance for most 

affected operators. 

This difference has been coordinated 

with Boeing. 

FAA’s Justification and Determination 

of the Effective Date 

Automatic retraction of the leading 

edge flaps could result in reduced climb 

performance during takeoff. Such a 

restriction could result in failure to 

achieve a minimum rate of climb, and 

consequent collision with terrain or 

obstacles or forced landing of the 

airplane. Because of our requirement to 

promote safe flight of civil aircraft and 

thus, the critical need to assure the 

proper functioning of the FCU and the 

short compliance time involved with 

this action, this AD must be issued 

immediately. 

Because an unsafe condition exists 

that requires the immediate adoption of 

this AD, and because no airplanes 

affected by this AD are on the U.S. 

Register, we find that notice and 

opportunity for prior public comment 

hereon are both impracticable and 

unnecessary and that good cause exists 

for making this amendment effective in 

less than 30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not provide you with notice and 

an opportunity to provide your 

comments before it becomes effective. 

However, we invite you to send any 

written data, views, or arguments about 

this AD. Send your comments to an 

address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2009–0556; Directorate Identifier 2009– 

NM–112–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this AD. We will consider all 

comments received by the closing date 

and may amend this 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 AD. 

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 AD: 


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Federal Register / Vol. 74, No. 124 / Tuesday, June 30, 2009 / Rules and Regulations 31171 

2009–13–03 Boeing: Amendment 39–15942. 

Docket No. FAA–2009–0556; Directorate 

Identifier 2009–NM–112–AD. 

Effective Date 

(a) This airworthiness directive (AD) is 

effective July 6, 2009. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Boeing Model 747– 

400 and –400F series airplanes, certificated 

in any category; Powered by Rolls-Royce 

RB211 series engines. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 78: Engine. 

Unsafe Condition 

(e) This AD results from a report of 

automatic retraction of the leading edge flaps 

during takeoff due to indications transmitted 

to the flap control unit (FCU) from the thrust 

reverser control system. The Federal Aviation 

Administration is issuing this AD to prevent 

automatic retraction of the leading edge flaps 

during takeoff, which could result in reduced 

climb performance and consequent collision 

with terrain and obstacles or forced landing 

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. 

Modification 

(g) Within 60 days after the effective date 

of this AD: Modify the thrust reverser control 

system wiring to the FCU in the P414 and 

P415 panels in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–78A2181, dated June 8, 

2009. 

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: 

Douglas Bryant, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue, SW., Renton, Washington 98057– 

3356; telephone (425) 917–6505; fax (425) 

917–6590. Or, e-mail information 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 Alert Service 

Bulletin 747–78A2181, dated June 8, 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 or 425–227–1152. 

(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 June 12, 

2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–15255 Filed 6–29–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2009–0066; Airspace 

Docket No. 09–ACE–1] 

Amendment of Class E Airspace; Ord, 

NE 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This action amends Class E 

airspace at Ord, NE. Additional 

controlled airspace is necessary to 

accommodate Area Navigation (RNAV) 

Standard Instrument Approach 

Procedures (SIAP) at Evelyn Sharp Field 

Airport, Ord, NE. This action also 

updates the geographic coordinates of 

the airport to coincide with the FAA’s 

National Aeronautical Charting Office. 

The FAA is taking this action to 

enhance the safety and management of 

Instrument Flight Rule (IFR) operations 

at Evelyn Sharp Field Airport. 

DATES: 0901 UTC, October 22, 2009. The 

Director of the Federal Register 

approves this incorporation by reference 

action under 1 CFR Part 51, subject to 

the annual revision of FAA Order 

7400.9 and publication of conforming 

amendments. 

FOR FURTHER INFORMATION CONTACT: 

Scott Enander, Central Service Center, 

Operations Support Group, Federal 

Aviation Administration, Southwest 

Region, 2601 Meacham Blvd., Fort 

Worth, TX 76137; telephone (817) 321– 

7716. 

SUPPLEMENTARY INFORMATION: 

History 

On April 21, 2009, the FAA published 

in the Federal Register a notice of 

proposed rulemaking to amend Class E 

airspace at Ord, NE, adding additional 

controlled airspace at Evelyn Sharp 

Field Airport, Ord, NE. (74 FR 18167, 

Docket No. FAA–2009–0066). Interested 

parties were invited to participate in 

this rulemaking effort by submitting 

written comments on the proposal to the 

FAA. No comments were received. Class 

E airspace designations are published in 

paragraph 6005 of FAA Order 7400.9S 

signed October 3, 2008, and effective 

October 31, 2008, which is incorporated 

by reference in 14 CFR Part 71.1. The 

Class E airspace designations listed in 

this document will be published 

subsequently in the Order. 

The Rule 

This action amends Title 14 Code of 

Federal Regulations (14 CFR) Part 71 by 

amending Class E airspace at Ord, NE, 

adding additional controlled airspace 

extending upward from 700 feet above 

the surface at Evelyn Sharp Field 

Airport, Ord, NE, for the safety and 

management of IFR operations. This 

action also updates the geographic 

coordinates of the airport to coincide 

with the FAA’s National Aeronautical 

Charting Office. 

The FAA has determined that this 

regulation only involves an established 

body of technical regulations for which 

frequent and routine amendments are 

necessary to keep them operationally 

current. Therefore, this regulation: (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) 

does not warrant preparation of a 

regulatory evaluation as the anticipated 

impact is so minimal. Since this is a 

routine matter that will only affect air 

traffic procedures and air navigation, it 

is certified that this rule, when 

promulgated, will not have a significant 

economic impact on a substantial 

number of small entities under the 

criteria of the Regulatory Flexibility Act. 


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