Federal Register / Vol. 74, No. 111 / Thursday, June 11, 2009 / Rules and Regulations 27693 

wiring of the normal supply fan and the low 

flow sensor for the equipment cooling system 

of the EFIS, by doing all the applicable 

actions specified in the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–21A1156, Revision 2, dated December 

11, 2008. 

Credit for Actions Done Using Previous 

Service Information 

(g)(1) Actions done before the effective date 

of this AD in accordance with Boeing Alert 

Service Bulletin 737–21A1156, Revision 1, 

dated October 23, 2007, are acceptable for 

compliance with the corresponding 

requirements of this AD. 

(2) For Groups 1 and 2 airplanes identified 

in Boeing Alert Service Bulletin 737– 

21A1156, Revision 1, dated October 23, 2007: 

Actions done before the effective date of this 

AD in accordance with Boeing Alert Service 

Bulletin 737–21A1156, dated June 20, 2006, 

are acceptable for compliance with the 

corresponding requirements of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(h)(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, ATTN: Suk 

Jang, Aerospace Engineer, Systems and 

Equipment Branch, ANM–130S, FAA, Seattle 

ACO, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

917–6511; fax (425) 917–6590; has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. 

(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 737–21A1156, Revision 2, dated 

December 11, 2008; 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 1, 

2009. 

Stephen P. Boyd, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E9–13304 Filed 6–10–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0612; Directorate 

Identifier 2008–NM–059–AD; Amendment 

39–15931; AD 2009–12–08] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 747 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for all 

Boeing Model 747 airplanes. This AD 

requires inspecting for cracks in the leftand right-side Stringer 11 longeron 

adjacent to the horizontal stabilizer 

pivot bulkhead, and related 

investigative and corrective actions if 

necessary. This AD results from a report 

of a crack found in the right-side 

Stringer 11 longeron horizontal flange, 

adjacent to the horizontal stabilizer 

pivot bulkhead, during a routine 

maintenance inspection. We are issuing 

this AD to detect and correct fatigue 

cracking of the longeron, which can 

propagate and cause damage to the 

adjacent horizontal stabilizer pivot 

bulkhead. This damage could result in 

loss of structural integrity and 

consequent inability of the bulkhead to 

carry flight loads, which could 

adversely affect controllability of the 

airplane. 

DATES: This AD becomes effective July 

16, 2009. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of July 16, 2009. 

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. You 

may review copies of the referenced 

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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (telephone 800–647–5527) 

is the Document Management Facility, 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: Ivan 

Li, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 917–6437; 

fax (425) 917–6590. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The FAA issued a supplemental 

notice of proposed rulemaking (NPRM) 

to amend 14 CFR part 39 to include an 

AD that would apply to all Boeing 

Model 747 airplanes. That supplemental 

NPRM was published in the Federal 

Register on February 20, 2009 (74 FR 

7834). That supplemental NPRM 

proposed to require inspecting for 

cracks in the left- and right-side Stringer 

11 longeron adjacent to the horizontal 

stabilizer pivot bulkhead, and doing 

related investigative and corrective 

actions if necessary. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comment received. The 

commenter, Boeing, concurs with the 

supplemental NPRM. 

Change to Supplemental NPRM 

We have added new paragraph (j) to 

this final rule and re-identified 

subsequent paragraphs to give credit for 

inspections accomplished using the 

original issue of Boeing Service Bulletin 

747–53A2703, dated February 14, 2008. 


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27694 Federal Register / Vol. 74, No. 111 / Thursday, June 11, 2009 / Rules and Regulations 

Conclusion 

We have carefully reviewed the 

available data, including the comment 

received, and determined that air safety 

and the public interest require adopting 

the AD with the changes described 

previously. We have determined that 

these changes will neither increase the 

economic burden on any operator nor 

increase the scope of the AD. 

Costs of Compliance 

We estimate that this AD affects 165 

airplanes of U.S. registry. We also 

estimate that it takes 3 work-hours per 

product to comply with this AD. The 

average labor rate is $80 per work-hour. 

Based on these figures, we estimate the 

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

be $39,600, or $240 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 have 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 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. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

See the ADDRESSES section for a location 

to examine the regulatory evaluation. 

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 Federal Aviation 

Administration (FAA) amends § 39.13 

by adding the following new 

airworthiness directive (AD): 

2009–12–08 Boeing: Amendment 39–15931. 

Docket No. FAA–2008–0612; Directorate 

Identifier 2008–NM–059–AD. 

Effective Date 

(a) This AD becomes effective July 16, 

2009. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to all Boeing Model 

747–100, 747–100B, 747–100B SUD, 747– 

200B, 747–200C, 747–200F, 747–300, 747– 

400, 747–400D, 747–400F, 747SR, and 747SP 

series airplanes, certificated in any category. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 53: Fuselage. 

Unsafe Condition 

(e) This AD results from a report of a crack 

found in the right-side Stringer 11 longeron 

horizontal flange, adjacent to the horizontal 

stabilizer pivot bulkhead, during a routine 

maintenance inspection. We are issuing this 

AD to detect and correct fatigue cracking of 

the longeron, which can propagate and cause 

damage to the adjacent horizontal stabilizer 

pivot bulkhead. This damage could result in 

loss of structural integrity and consequent 

inability of the bulkhead to carry flight loads, 

which could adversely affect controllability 

of the airplane. 

Compliance 

(f) Comply with this AD within the 

compliance times specified, unless already 

done. 

Inspection/Related Investigative and 

Corrective Actions 

(g) Except as provided by paragraph (h) of 

this AD: At the applicable times specified in 

paragraph 1.E. of Boeing Service Bulletin 

747–53A2703, Revision 1, dated September 

16, 2008, do a surface high frequency eddy 

current (HFEC) inspection for cracks in the 

left- and right-side Stringer 11 longeron 

exposed surfaces and edges between Station 

2598 and 2607 adjacent to the horizontal 

stabilizer pivot bulkhead; and do all 

applicable related investigative and 

corrective actions before further flight, in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 747– 

53A2703, Revision 1, dated September 16, 

2008, except as provided by paragraph (i) of 

this AD. 

Exception to Compliance Times 

(h) Where Boeing Service Bulletin 747– 

53A2703, Revision 1, dated September 16, 

2008, specifies counting the compliance time 

from ‘‘ * * * the date on this service 

bulletin,’’ this AD requires counting the 

compliance time from the effective date of 

this AD. 

Exception to Corrective Actions 

(i) If any crack is found during any 

inspection required by this AD, and Boeing 

Service Bulletin 747–53A2703, Revision 1, 

dated September 16, 2008, specifies to 

contact Boeing for appropriate action: Before 

further flight, repair using a method 

approved in accordance with the procedures 

specified in paragraph (k) of this AD. 

Actions Accomplished According to 

Previous Issue of Service Bulletin 

(j) Inspections, related investigative 

actions, and corrective actions accomplished 

before the effective date of this AD according 

to Boeing Alert Service Bulletin 747– 

53A2703, dated February 14, 2008, are 

considered acceptable for compliance with 

the corresponding actions specified in 

paragraph (g) of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(k)(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, ATTN: Ivan 

Li, Aerospace Engineer, Airframe Branch, 

ANM–120S, FAA, Seattle ACO, 1601 Lind 

Avenue, SW., Renton, Washington 98057– 

3356; telephone (425) 917–6437; fax (425) 

917–6590 has the authority to approve 

AMOCs for this AD, if requested using the 

procedures found in 14 CFR 39.19. Or, e-mail 

information to 9-ANM-Seattle-ACO-AMOCRequests@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), 

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 


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Federal Register / Vol. 74, No. 111 / Thursday, June 11, 2009 / Rules and Regulations 27695 

required by this AD, if it is approved by an 

Authorized Representative for the Boeing 

Commercial Airplanes Delegation Option 

Authorization Organization who 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 

(l) You must use Boeing Service Bulletin 

747–53A2703, Revision 1, dated September 

16, 2008, 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 2, 

2009. 

Stephen P. Boyd, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E9–13406 Filed 6–10–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–1237; Directorate 

Identifier 2008–NM–125–AD; Amendment 

39–15932; AD 2009–12–09] 

RIN 2120–AA64 

Airworthiness Directives; ATR Model 

ATR42–200, ATR42–300, ATR42–320, 

ATR42–500, ATR72–101, ATR72–201, 

ATR72–102, ATR72–202, ATR72–211, 

ATR72–212, and ATR72–212A 

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: 

* * * * * 

[C]hafed wirings were found in the rear 

baggage zone, closed [close] to the forward 

side of the aft pressure bulkhead, due to 

contact with an understructure securing 

screw. The concerned wiring harness 

includes rudder trim, pitch trim and stick 

pusher control wires. Damages on those 

wires might lead to the loss of fail safe 

criteria for those critical functions. 

* * * * * 

The unsafe condition is reduced 

controllability of the airplane. We are 

issuing this AD to require actions to 

correct the unsafe condition on these 

products. 

DATES: This AD becomes effective July 

16, 2009. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of July 16, 2009. 

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: Tom 

Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1137; 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 November 26, 2008 (73 FR 

71961). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

One ATR operator reported some spurious 

‘‘Pitch disconnect’’ warning and ‘‘AIL and R 

ELEV’’ Anti-Ice Horn Fault caution 

annunciations which precluded the use of 

the autopilot. 

During the investigation, chafed wirings 

were found in the rear baggage zone, closed 

[close] to the forward side of the aft pressure 

bulkhead, due to contact with an 

understructure securing screw. The 

concerned wiring harness includes rudder 

trim, pitch trim and stick pusher control 

wires. Damages on those wires might lead to 

the loss of fail safe criteria for those critical 

functions. 

To address the identified unsafe condition, 

this AD mandates a one-time inspection and 

a routing modification of the electrical wires 

in the bulkhead area. 

The unsafe condition is reduced 

controllability of the airplane. The 

corrective action also includes 

contacting ATR for repair instructions 

and doing the repair if any damage 

(chafing or contact between bundles of 

cables and the airframe structure) is 

found during the one-time inspection. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Explanation of Change to the NPRM 

We have revised paragraph (c) of the 

AD to coincide with the effectivity of 

the European Aviation Safety Agency 

(EASA) AD. 

Explanation of Revised Service 

Information 

ATR has issued the service bulletins 

identified in the following table. 

TABLE—REVISED SERVICE INFORMATION

ATR Service Bulletin— Revision— Dated— 

ATR42–92–0015, including Accomplishment Report ........................................................................................... 01 February 11, 2009. 

ATR42–92–0018, including Accomplishment Report ........................................................................................... 01 September 4, 2008. 

ATR42–92–0018, including Accomplishment Report ........................................................................................... 02 February 13, 2009. 

ATR72–92–1016, including Accomplishment Report ........................................................................................... 01 February 11, 2009. 


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