38404 Federal Register / Vol. 75, No. 127 / Friday, July 2, 2010 / Rules and Regulations 

(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 June 17, 

2010. 

Robert D. Breneman, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–15935 Filed 7–1–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0641; Directorate 

Identifier 2010–NM–130–AD; Amendment 

39–16354; AD 2010–14–09] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 747–100B, 747–200B, 

747–200F, 747–300, 747–400, 747– 

400F, and 747SP Series Airplanes 

Equipped with Rolls-Royce RB211–524 

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 

Model 747–100B, 747–200B, 747–200F, 

747–300, 747–400, 747–400F, and 

747SP series airplanes. This AD requires 

repetitive detailed and high frequency 

eddy current inspections of the forward 

and aft sides of the strut front spar 

chord for cracks and fractures at each 

strut location, and corrective actions if 

necessary. This AD results from reports 

of cracks and fractures in the nacelle 

strut front spar chord assembly. We are 

issuing this AD to detect and correct 

cracks and fractures of the nacelle strut 

front spar chord assembly. Fracture of 

the front spar chord assembly could 

lead to loss of the strut upper link load 

path and consequent fracture of the 

diagonal brace, which could result in inflight separation of the strut and engine 

from the airplane. 

DATES: This AD is effective July 19, 

2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of July 19, 2010. 

We must receive comments on this 

AD by August 16, 2010. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue, SE., Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue, SE., Washington, DC 20590, 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

For service information identified in 

this 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: Ken 

Paoletti, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 917–6434; 

fax (425) 917–6590. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We have received a report that an 

operator found a cracked strut number 

2 upper chord on a Rolls-Roycepowered airplane while accomplishing 

the actions specified in Boeing Service 

Bulletin 747–54–2213. The upper chord 

was 50 percent cracked and had to be 

replaced. The airplane had accumulated 

approximately 10,500 total flight cycles 

and 83,700 total flight hours. 

In addition, two other operators 

reported finding two cracks on two 

Rolls-Royce RB211-powered airplanes 

on the strut number 1 upper chord. Both 

cracks were repaired and neither upper 

chord had to be replaced. The upper 

chords on these two airplanes had 

accumulated approximately 9,300 and 

16,100 total flight cycles and 78,100 and 

56,700 total flight hours respectively. 

This condition, if not corrected, could 

result in the loss of the strut upper link 

load path. Continued operation without 

the strut upper link load path could 

result in the fracture of the diagonal 

brace, and subsequent separation of the 

strut and engine from the airplane 

during flight. 

Relevant Service Information 

We reviewed Boeing Alert Service 

Bulletin 747–54A2224, Revision 3, 

dated May 20, 2010. Revision 3 of this 

service bulletin was issued, among other 

reasons, to add Model 747–100B, 747– 

200B, 747–200F, 747–300, 747–400, 

747–400F, and 747SP equipped with 

Rolls-Royce RB211–524 series engines. 

This service bulletin describes 

procedures for repetitive detailed 

inspections and high frequency eddy 

current (HFEC) inspections of the 

forward and aft sides of the strut front 

spar chord assemblies for cracks and 

fractures at each strut location, and 

corrective actions if necessary. 

Corrective actions include contacting 

Boeing for additional instructions if any 

crack or fracture is found, and repairing 

any cracks and fractures. 

Other Related Rulemaking 

On December 30, 2009, we issued AD 

2010–01–10, Amendment 39–16168 (75 

FR 3150, January 20, 2010), applicable 

to certain Model 747–100, 747–100B, 

747–100B SUD, 747–200B, 747–200C, 

747–200F, 747–300, 747SR, and 747SP 

series airplanes equipped with General 

Electric (GE) CF6–45 or –50 series 

engines, or equipped with Pratt & 

Whitney JT9D–3 or –7 (excluding –70) 

series engines. That AD currently 

requires repetitive inspections to detect 

cracks and fractures of the strut front 

spar chord assembly (including the 

forward side) at each strut location, and 


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Federal Register / Vol. 75, No. 127 / Friday, July 2, 2010 / Rules and Regulations 38405 

repair if necessary. That AD requires a 

one-time inspection for cracking of the 

forward side of the front spar chord 

assembly on the inboard and outboard 

struts, installation of a cap skin doubler 

for certain airplanes, and repair if 

necessary. Certain actions provided in 

that AD terminate the repetitive 

inspections of the forward side of the 

strut front spar chord assembly; the 

inspections of the aft side assembly are 

not terminated and continue to be 

required. That AD referred to Boeing 

Alert Service Bulletin 747–54A2224, 

Revision 1, dated November 16, 2006, to 

address the identified unsafe condition 

on Model 747–100, 747–100B, 747– 

100B SUD, 747–200B, 747–200C, 747– 

200F, 747–300, 747SR, and 747SP series 

airplanes equipped with GE CF6–45 or 

–50 series engines, or equipped with 

Pratt & Whitney JT9D–3 or –7 

(excluding –70) series engines. 

FAA’s Determination and Requirements 

of This AD 

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 in other products of these same 

type designs. This AD requires 

accomplishing the actions specified in 

the service information described 

previously, except as discussed under 

‘‘Differences Between the AD and the 

Service Information.’’ 

Differences Between the AD and the 

Service Information 

Boeing Alert Service Bulletin 747– 

54A2224, Revision 3, dated May 20, 

2010, specifies to contact the 

manufacturer for instructions on how to 

repair certain conditions, but this AD 

would require repairing those 

conditions in one of the following ways: 

• In accordance with a method that 

we approve; or 

• Using data that meet the 

certification basis of the airplane, and 

that have been approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) whom 

we have authorized to make those 

findings. 

Interim Action 

We consider this AD interim action. If 

final action is later identified, we might 

consider further rulemaking then. 

FAA’s Justification and Determination 

of the Effective Date 

Continued operation without the strut 

upper link load path could result in the 

fracture of the diagonal brace, and 

subsequent separation of the strut and 

engine from the airplane during flight. 

Because of our requirement to promote 

safe flight of civil aircraft and thus, the 

critical need to assure structural 

integrity of the engine support structure 

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, we find that notice and 

opportunity for prior public comment 

hereon are impracticable 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– 

2010–0641; Directorate Identifier 2010– 

NM–130–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: 

2010–14–09 The Boeing Company: 

Amendment 39–16354. Docket No. 

FAA–2010–0641; Directorate Identifier 

2010–NM–130–AD. 

Effective Date 

(a) This airworthiness directive (AD) is 

effective July 19, 2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to The Boeing 

Company Model 747–100B, 747–200B, 747– 

200F, 747–300, 747–400, 747–400F, and 

747SP series airplanes; certificated in any 

category; equipped with Rolls-Royce RB211– 

524 series engines; as identified in Boeing 

Alert Service Bulletin 747–54A2224, 

Revision 3, dated May 20, 2010. 


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38406 Federal Register / Vol. 75, No. 127 / Friday, July 2, 2010 / Rules and Regulations 

Subject 

(d) Air Transport Association (ATA) of 

America Code 54: Nacelles/Pylons. 

Unsafe Condition 

(e) This AD results from reports of cracks 

and fractures in the nacelle strut front spar 

chord assembly. The Federal Aviation 

Administration is issuing this AD to detect 

and correct cracks and fractures of the 

nacelle strut front spar chord assembly. 

Fracture of the front spar chord assembly 

could lead to loss of the strut upper link load 

path and consequent fracture of the diagonal 

brace, which could result in in-flight 

separation of the strut and engine from 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. 

Inspections of the Forward and Aft Sides of 

the Strut Front Spar Chord Assemblies 

(g) Before the accumulation of 8,000 total 

flight cycles, or within 90 days after the 

effective date of this AD, whichever occurs 

later: Perform a detailed inspection and a 

high frequency eddy current (HFEC) 

inspection for cracking or fracturing in the 

forward and aft sides of the strut front spar 

chord, in accordance with Parts 1 and 2 of 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin 747–54A2224, 

Revision 3, dated May 20, 2010. If no 

cracking or fracturing is found, repeat the 

inspections thereafter at intervals not to 

exceed 1,500 flight cycles. 

Corrective Actions 

(h) If any crack or fracture is found during 

any inspection required by this AD: Before 

further flight, repair the crack or fracture 

using a method approved in accordance with 

the procedures specified in paragraph (i) of 

this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(i)(1) The Manager, Seattle 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: Ken 

Paoletti, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle Aircraft 

Certification Office, 1601 Lind Avenue, SW., 

Renton, Washington 98057–3356; telephone 

(425) 917–6434; 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. 

(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, Seattle 

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. 

Material Incorporated by Reference 

(j) You must use Boeing Alert Service 

Bulletin 747–54A2224, Revision 3, dated 

May 20, 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 June 21, 

2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–16046 Filed 7–1–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2010–0071; Airspace 

Docket No. 10–AAL–1] 

RIN 2120–AA66 

Amendment of Norton Sound Low and 

Control 1234L Offshore Airspace 

Areas; Alaska 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This action modifies the 

Norton Sound Low and Control 1234L 

Offshore Airspace Areas in Alaska. This 

action will lower the airspace floors to 

provide controlled airspace beyond 12 

miles from the coast of the United States 

given that there is a requirement to 

provide Instrument Flight Rules (IFR) en 

route Air Traffic Control (ATC) services 

and within which the United States is 

applying domestic ATC procedures. 

DATES: Effective date 0901 UTC, 

September 23, 2010. 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: Ken 

McElroy, Airspace and Rules Group, 

Office of System Operations Airspace 

and AIM, Federal Aviation 

Administration, 800 Independence 

Avenue, SW., Washington, DC 20591; 

telephone: (202) 267–8783. 

SUPPLEMENTARY INFORMATION: 

History 

On Wednesday, March 31, 2010, the 

FAA published in the Federal Register 

a notice of proposed rulemaking 

(NPRM) to modify two Alaskan Offshore 

Airspace Areas, Norton Sound Low, and 

Control 1234L (75 FR 16024). Interested 

parties were invited to participate in 

this rulemaking effort by submitting 

written comments on the proposal. No 

comments were received. With the 

exception of editorial changes, this 

amendment is the same as that proposed 

in the NPRM. 

The Rule 

This action amends Title 14 Code of 

Federal Regulations (14 CFR) part 71 by 

modifying the Norton Sound Low and 

Control 1234L Offshore Airspace Areas 

in Alaska. 

The Norton Sound Low Offshore 

Airspace Area will be modified by 

lowering the offshore airspace floor to 

1,200 feet mean sea level (MSL) at the 

following airports; within 73 miles of 

Clarks Point, King Salmon, Kivalina, 

Kwethluk, Napakiak, Scammon Bay, 

Shaktooklik, and Tooksook Bay; within 

74 miles of Elim and Manokotak, and 

within 72.5 miles of Red Dog. 

The Control 1234L Offshore Airspace 

Area will be modified by lowering the 

offshore airspace floor to 1,200 feet 

above the surface within 73 miles of 

Nikolski, and Toksook Bay Airports. 

Offshore airspace areas are published 

in paragraph 2003 of FAA Order 

7400.9T dated August 27, 2009 and 

effective September 15, 2009, which is 

incorporated by reference in 14 CFR 

71.1. The offshore airspace areas listed 

in this document will be published 

subsequently in the Order. 

The FAA has determined that this 

regulation only involves an established 

body of technical regulations for which 


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