49708 Federal Register / Vol. 77, No. 160 / Friday, August 17, 2012 / Rules and Regulations 

6030, or go to http://www.archives.gov/

federal_register/code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on August 

3, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–19815 Filed 8–16–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0490; Directorate 

Identifier 2012–NM–066–AD; Amendment 

39–17159; AD 2012–16–12] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all The 

Boeing Company Model 707 airplanes, 

and Model 720 and 720B series 

airplanes. This AD was prompted by 

reports of cracking of the midspar 

fittings, and of the engine and nacelle 

strut separating from the airplane. This 

AD requires performing a detailed 

inspection of the midspar fittings of the 

nacelle strut to confirm that the correct 

part number is installed, and installing 

the correct part number if necessary; 

performing repetitive high frequency 

eddy current (HFEC) inspections of the 

midspar fittings of the nacelle strut for 

cracks, and repair if necessary; and 

performing repetitive general visual 

inspections of the nacelle struts to verify 

that the nacelle strut has not drooped 

below its normal position, applying the 

droop stripe to the nacelle strut and 

sailboat fairing if necessary, and 

performing repair if necessary. We are 

issuing this AD to detect and correct 

cracking of the midspar fitting, which 

could result in separation of the nacelle 

strut and engine from the airplane while 

in flight, and consequent loss of 

controllability of the airplane. 

DATES: This AD is effective September 

21, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of September 21, 2012. 

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; 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. 

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 (phone: 800–647–5527) is 

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: 

Berhane Alazar, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: (425) 917–6577; 

fax: (425) 917–6590; email: 

Berhane.Alazar@faa.gov. 

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 published in the Federal 

Register on May 30, 2012 (77 FR 31762). 

That NPRM proposed to require 

performing a detailed inspection of the 

midspar fittings of the nacelle strut to 

confirm that the correct part number is 

installed, and installing the correct part 

number if necessary; performing 

repetitive HFEC inspections of the 

midspar fittings of the nacelle strut for 

cracks, and repair if necessary; and 

performing repetitive general visual 

inspections of the nacelle struts to verify 

that the nacelle strut has not drooped 

below its normal position, applying the 

droop stripe to the nacelle strut and 

sailboat fairing if necessary, and 

performing repair if necessary. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

have considered the comments received. 

Boeing and the National Transportation 

Safety Board support the NPRM. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Costs of Compliance 

We estimate that this AD affects 11 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. 

operators 

Detailed inspection, repetitive HFEC inspections, and repetitive general visual inspections of the midspar fittings 

of the nacelle strut.

23 work-hours × $85 per hour = $1,955, 

per inspection.

$0 $1,955, per inspection.$21,505, per inspection. 

We estimate the following costs to do 

any necessary repairs that would be 

required based on the results of the 

inspections. We have no way of 

determining the number of aircraft that 

might need these repairs: 


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Federal Register / Vol. 77, No. 160 / Friday, August 17, 2012 / Rules and Regulations 49709 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Install the correct part 

number.

130 work-hours × $85 per hour = $11,050 .......... $7,867 × 4 = $31,468 ........................................... $42,518 

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), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) 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. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

2012–16–12 The Boeing Company: 

Amendment 39–17159; Docket No. 

FAA–2012–0490; Directorate Identifier 

2012–NM–066–AD. 

(a) Effective Date 

This AD is effective September 21, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all The Boeing 

Company Model 707–100 long body, –200, 

–100B long body, and –100B short body 

series airplanes; Model 707–300, –300B, 

–300C, and –400 series airplanes; and Model 

720 and 720B series airplanes; certificated in 

any category. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 54, Nacelles/Pylons. 

(e) Unsafe Condition 

This AD was prompted by reports of 

cracking of the midspar fittings and of the 

engine and nacelle strut separating from the 

airplane. We are issuing this AD to detect 

and correct cracking of the midspar fitting, 

which could result in separation of the 

nacelle strut and engine from the airplane 

while in flight, and consequent loss of 

controllability of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Detailed Inspection 

Within 120 days after the effective date of 

this AD: Do a detailed inspection of the 

midspar fittings of engine numbers 2 and 3 

nacelle struts to confirm that the correct part 

number is installed, in accordance with the 

Accomplishment Instructions of Boeing 707 

Alert Service Bulletin A3537, dated January 

30, 2012 (which is not incorporated by 

reference in this AD). If any incorrect part 

number is found: Before further flight, install 

the correct part number, in accordance with 

the Accomplishment Instructions of Boeing 

707 Alert Service Bulletin A3537, dated 

January 30, 2012. 

Note 1 to paragraph (g) of this AD: Boeing 

707 Alert Service Bulletin A3537, dated 

January 30, 2012, refers to Boeing 707/720 

Service Bulletin 3183, Revision 5, dated 

September 16, 1993 (which is not 

incorporated by reference in this AD), as an 

additional source of guidance for high 

frequency eddy current (HFEC) inspections 

of the midspar fittings of engine numbers 2 

and 3 nacelle struts for cracks. 

(h) HFEC Inspection 

At the applicable times specified in 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 707 

Alert Service Bulletin A3537, dated January 

30, 2012, except as provided in paragraph (j) 

of this AD: Do an HFEC inspection of the 

midspar fittings of engine numbers 2 and 3 

nacelle struts for cracks, in accordance with 

the Accomplishment Instructions of Boeing 

707 Alert Service Bulletin A3537, dated 

January 30, 2012, except as provided by 

paragraph (k) of this AD. If any crack is 

found, before further flight, repair using a 

method approved in accordance with the 

procedures specified in paragraph (m) of this 

AD. Thereafter, repeat the inspection at the 

applicable intervals specified in paragraph 

1.E., ‘‘Compliance,’’ of Boeing 707 Alert 

Service Bulletin A3537, dated January 30, 

2012. 

(i) General Visual Inspection of the Nacelle 

Struts of Engine Numbers 1, 2, 3, and 4 

At the applicable times specified in 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 707 

Alert Service Bulletin A3537, dated January 

30, 2012, except as provided in paragraph (j) 

of this AD: Do a general visual inspection of 

the nacelle struts of engine numbers 1, 2, 3, 

and 4 to verify that the nacelle strut has not 

drooped below its normal position, in 

accordance with the Accomplishment 

Instructions of Boeing 707 Alert Service 

Bulletin A3537, dated January 30, 2012. 

Thereafter, repeat the inspection at the 

applicable intervals specified in paragraph 

1.E., ‘‘Compliance,’’ of Boeing 707 Alert 

Service Bulletin A3537, dated January 30, 

2012. 

(1) If any nacelle strut has drooped below 

its normal position: Before further flight, 

repair using a method approved in 

accordance with the procedures specified in 

paragraph (m) of this AD. 

(2) If any nacelle strut has not drooped 

below its normal position, and no droop 

stripe specified in Boeing 707/720 Service 

Bulletin 3377, dated November 21, 1979 

(which is not incorporated by reference in 

this AD) has been applied: At the applicable 

times in paragraph 1.E., ‘‘Compliance,’’ of 

Boeing 707 Alert Service Bulletin A3537, 

dated January 30, 2012, except as provided 


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49710 Federal Register / Vol. 77, No. 160 / Friday, August 17, 2012 / Rules and Regulations 

in paragraph (j) of this AD: Apply the droop 

stripe to the nacelle strut and sailboat fairing, 

on each side of engine numbers 1, 2, 3, and 

4 nacelle struts, in accordance with the 

Accomplishment Instructions of Boeing 707 

Alert Service Bulletin A3537, dated January 

30, 2012. 

(j) Exception to the Compliance Times 

Where Boeing 707 Alert Service Bulletin 

A3537, dated January 30, 2012, specifies a 

compliance time based on ‘‘the original issue 

date of this service bulletin,’’ this AD 

requires compliance within the specified 

compliance time after the effective date of 

this AD. 

(k) Exception to the Service Information 

Where Boeing 707 Alert Service Bulletin 

A3537, dated January 30, 2012, refers to 

‘‘Manual 707, 720 NDT Part 6, 51–00–00 

Figure 24 as an accepted procedure’’ for the 

HFEC inspection, this AD requires that the 

inspection be done in accordance with Figure 

24, Steel Part Surface Inspection (Impedance 

Plane Display), Subject 51–00–00, StructuralGeneral, of Part 6, Eddy Current, of the 

Boeing 707/720 Nondestructive Test Manual, 

Document D6–48023, Revision 120, dated 

March 15, 2012. 

(l) Credit for Previous Actions 

This paragraph provides credit for the 

installation of the engine droop lines 

required by paragraph (i) of this AD, if those 

actions were performed before the effective 

date of this AD using Boeing 707/720 Service 

Bulletin 3377, dated November 21, 1979 

(which is not incorporated by reference in 

this AD). 

(m) Alternative Methods of Compliance 

(AMOCs) 

(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. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(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. 

(n) Related Information 

(1) For more information about this AD, 

contact Berhane Alazar, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: (425) 917–6577; fax: (425) 917–6590; 

email: Berhane.Alazar@faa.gov. 

(2) For service information identified in 

this AD, that is not incorporated by reference 

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; 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. 

(o) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

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

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Boeing 707 Alert Service Bulletin 

A3537, dated January 30, 2012. 

(ii) Figure 24, Steel Part Surface Inspection 

(Impedance Plane Display), Subject 51–00– 

00, Structural—General, of Part 6, Eddy 

Current, of the Boeing 707/720 

Nondestructive Test Manual, Document D6– 

48023, Revision 120, dated March 15, 2012. 

The revision level of this document is 

identified on only the manual revision 

Transmittal Sheet. 

(3) For The Boeing Company 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; Internet https:// 

www.myboeingfleet.com. 

(4) You may view this service information 

at FAA, 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 view this 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/cfr/ 

index.html. 

Issued in Renton, Washington, on August 

3, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–19819 Filed 8–16–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0517; Directorate 

Identifier 2009–SW–73–AD; Amendment 39– 

17137; AD 2012–15–08] 

RIN 2120–AA64 

Airworthiness Directives; Sikorsky 

Aircraft Corporation Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for 

Sikorsky Aircraft Corporation (Sikorsky) 

Model S–76A helicopters to require 

modifying the electric rotor brake (ERB) 

and inserting changes into the ‘‘Normal 

Procedures’’ and ‘‘Emergency 

Procedures’’ sections of the Rotorcraft 

Flight Manual (RFM). This AD was 

prompted by a fire in the main gearbox 

area as a result of a hot electric rotor 

brake (ERB). The actions are intended to 

prevent overheating of the ERB, ignition 

of the ERB hydraulic fluid, a fire in the 

main gearbox area, and subsequent loss 

of control of the helicopter. 

DATES: This AD is effective September 

21, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain documents listed in this AD 

as of September 21, 2012. 

ADDRESSES: For service information 

identified in this AD, contact Sikorsky 

Aircraft Corporation, Attn: Manager, 

Commercial Technical Support, 

mailstop s581a, 6900 Main Street, 

Stratford, CT 06614; telephone (800) 

562–4409; email 

tsslibrary@sikorsky.com; or at http:// 

www.sikorsky.com. You may review the 

referenced service information at the 

FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham 

Blvd., Room 663, Fort Worth, Texas 

76137. 

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 this AD, any 

incorporated-by-reference service 

information, the economic evaluation, 

any comments received, and other 

information. The street address for the 

Docket Operations Office (phone: 800– 

647–5527) is U.S. Department of 

Transportation, Docket Operations 

Office, M–30, West Building Ground 


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