This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

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Rules and Regulations Federal Register

10499 

Vol. 78, No. 31 

Thursday, February 14, 2013 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1110; Directorate 

Identifier 2012–NM–013–AD; Amendment 

39–17353; AD 2013–03–19] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

certain The Boeing Company Model 707 

airplanes, and Model 720 and 720B 

series airplanes. That AD currently 

requires replacing wiring for the fuel 

boost pumps and override pumps with 

new wiring, installing Teflon sleeving 

on the wiring, and doing associated 

actions; and doing repetitive inspections 

to detect damage of the wiring or 

evidence of a fuel leak. This new AD 

reduces the repetitive inspection 

interval. This AD was prompted by a 

determination that an inspection 

interval must be reduced. We are 

issuing this AD to detect and correct 

damaged wiring for the fuel boost 

pumps and override pumps, which 

could cause electrical arcing that could 

puncture the conduit containing the 

wire, and result in a fuel tank explosion 

or a fire adjacent to the fuel tank. 

DATES: This AD is effective March 21, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of October 1, 2001 (66 FR 44954, 

August 27, 2001). 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P. O. Box 3707, 

MC 2H–65, Seattle, WA 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, WA. 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: 

Rebel Nichols, Aerospace Engineer, 

Propulsion Branch, ANM–140S, Seattle 

Aircraft Certification Office (ACO), 

FAA, 1601 Lind Avenue SW., Renton, 

WA 98057–3356; phone: 425–917–6509; 

fax: 425–917–6590; email: 

Rebel.Nichols@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2001–17–20, 

Amendment 39–12411 (66 FR 44954, 

August 27, 2001). That AD applies to 

the specified products. The NPRM 

published in the Federal Register on 

October 29, 2012 (77 FR 65501). That 

NPRM proposed to continue to require 

replacing wiring for the fuel boost 

pumps and override pumps with new 

wiring, installing Teflon sleeving on the 

wiring, and doing associated actions; 

and doing repetitive inspections to 

detect damage of the wiring or evidence 

of a fuel leak with a reduced repetitive 

inspection interval. 

Comment 

We gave the public the opportunity to 

participate in developing this AD. We 

have considered the comment received. 

Boeing stated that it has reviewed the 

NPRM (77 FR 65501, October 29, 2012), 

and concurs with the proposed rule. 

Conclusion 

We reviewed the relevant data, 

considered the comment received, and 

determined that air safety and the 

public interest require adopting the AD 

as proposed—except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (77 FR 

65501, October 29, 2012) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (77 FR 65501, 

October 29, 2012). 

Costs of Compliance 

We estimate that this AD affects 5 

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 

Replacement [retained action from AD 

2001–17–20, Amendment 39–12411 

(66 FR 44954, August 27, 2001)].

38 work-hours × $85 per hour = $3,230 $9,943 $13,173 .................. $65,865. 

Inspection [retained action from AD 

2001–17–20, Amendment 39–12411 

(66 FR 44954, August 27, 2001)].

3 work-hours × $85 per hour = $255 

per inspection cycle.

$0 $255 per inspection 

cycle.

$1,275 per inspection cycle. 

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10500 Federal Register / Vol. 78, No. 31 / Thursday, February 14, 2013 / Rules and Regulations 

The new requirements of this AD add 

no additional economic burden. The 

increase in replacement labor costs of 31 

work hours in AD 2001–17–20, 

Amendment 39–12411 (66 FR 44954, 

August 27, 2001), to the 38 work hours 

specified in this AD, is due to the 

opening and closing hours being 

included in the cost of this AD. We have 

received no definitive data that would 

enable us to provide cost estimates for 

the on-condition actions specified in 

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 

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), 

(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 

removing airworthiness directive (AD) 

2001–17–20, Amendment 39–12411 (66 

FR 44954, August 27, 2001), and adding 

the following new AD: 

2013–03–19 The Boeing Company: 

Amendment 39–17353; Docket No. 

FAA–2012–1110; Directorate Identifier 

2012–NM–013–AD. 

(a) Effective Date 

This AD is effective March 21, 2013. 

(b) Affected ADs 

This AD supersedes AD 2001–17–20, 

Amendment 39–12411 (66 FR 44954, August 

27, 2001). 

(c) Applicability 

This AD applies to 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; line 

numbers 1 through 941 inclusive. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 24, Electrical Power. 

(e) Unsafe Condition 

This AD was prompted by a report that, 

while investigating a fuel leak around the 

bolts on the number 1 fuel boost pump on 

a Boeing Model 707 series airplane, an 

operator found wire damage where the fuel 

boost pump wiring exited the boost pump 

and entered the boost pump access area. We 

are issuing this AD to detect and correct 

damaged wiring for the fuel boost pumps and 

override pumps, which could cause electrical 

arcing that could puncture the conduit 

containing the wire, and result in a fuel tank 

explosion or a fire adjacent to the fuel tank. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Replacement of Wiring, 

Installation of Sleeving, and Associated 

Actions 

This paragraph restates the requirements of 

paragraph (a) of AD 2001–17–20, 

Amendment 39–12411 (66 FR 44954, August 

27, 2001). Within 1 year or 4,000 flight hours 

after October 1, 2001 (the effective date of AD 

2001–17–20), whichever occurs first: Replace 

the wiring for the fuel boost pumps and 

override pumps, install Teflon sleeving over 

the wiring, and do all associated actions, per 

the Accomplishment Instructions of Boeing 

Service Bulletin A3500, Revision 1, dated 

April 26, 2001. The associated actions 

include performing a general visual 

inspection of the area around each fuel boost 

pump and override pump for evidence of a 

fuel leak; finding the source of any fuel leak 

and repairing the affected area; replacing the 

conduit, if required; and performing a 

detailed visual inspection of the wiring 

installed in the conduit for evidence of 

electrical arcing or a fuel leak, or exposed 

copper wire. If replacement of the conduit is 

deferred per the Accomplishment 

Instructions of Boeing Service Bulletin 

A3500, Revision 1, dated April 26, 2001, 

repeat the inspection for fuel leaks every 500 

flight hours until the conduit is replaced, and 

replace the conduit within 6,000 flight hours 

or 18 months, whichever occurs first. 

(1) For the purposes of this AD, a general 

visual inspection is defined as: ‘‘A visual 

examination of an interior or exterior area, 

installation, or assembly to detect obvious 

damage, failure, or irregularity. This level of 

inspection is made under normally available 

lighting conditions such as daylight, hangar 

lighting, flashlight, or drop-light, and may 

require removal or opening of access panels 

or doors. Stands, ladders, or platforms may 

be required to gain proximity to the area 

being checked.’’ 

(2) For the purposes of this AD, a detailed 

visual inspection is defined as: ‘‘An intensive 

visual examination of a specific structural 

area, system, installation, or assembly to 

detect damage, failure, or irregularity. 

Available lighting is normally supplemented 

with a direct source of good lighting at 

intensity deemed appropriate by the 

inspector. Inspection aids such as mirror, 

magnifying lenses, etc., may be used. Surface 

cleaning and elaborate access procedures 

may be required.’’ 

(h) Retained Repetitive Inspections 

This paragraph restates the requirements of 

paragraph (b) of AD 2001–17–20, 

Amendment 39–12411 (66 FR 44954, August 

27, 2001), with a new compliance time. After 

replacement of the wiring per paragraph (g) 

of this AD, repeat the detailed visual 

inspection of the wiring for the fuel boost 

pumps and override pumps for damage, such 

as evidence of electrical arcing or exposed 

copper wire, or evidence of a fuel leak. After 

the effective date of this AD, repeat the 

inspection one time at the earlier of the times 

specified in paragraphs (h)(1) and (h)(2) of 

this AD, per the Accomplishment 

Instructions of Boeing Service Bulletin 

A3500, Revision 1, dated April 26, 2001. If 

any electrical arcing or exposed copper wire 

or evidence of a fuel leak is detected during 

any inspection per this paragraph, before 

further flight, do the applicable corrective 

actions (including finding the source of any 

fuel leak and repairing the affected area, 

replacing the wiring, replacing the conduit, 

or installing new Teflon sleeving; as 

applicable) according to the Accomplishment 

Instructions of Boeing Service Bulletin 

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Federal Register / Vol. 78, No. 31 / Thursday, February 14, 2013 / Rules and Regulations 10501 

A3500, Revision 1, dated April 26, 2001. 

Repeat the inspection thereafter at intervals 

not to exceed 15,000 flight hours. 

(1) Within 30,000 flight hours after the 

most recent inspection. 

(2) At the later of the compliance times 

specified in paragraphs (h)(2)(i) and (h)(2)(ii) 

of this AD. 

(i) Within 15,000 flight hours after the most 

recent inspection. 

(ii) Within 3 years after the effective date 

of this AD. 

(i) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraph (g) of this AD, 

if those actions were performed before 

October 1, 2001 (the effective date of AD 

2001–17–20, Amendment 39–12411 (66 FR 

44954, August 27, 2001)), using Boeing Alert 

Service Bulletin A3500, dated July 27, 2000, 

which is not incorporated by reference in this 

AD. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle 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) AMOCs approved previously in 

accordance with AD 2001–17–20, 

Amendment 39–12411 (66 FR 44954, August 

27, 2001), are approved as AMOCs for the 

corresponding provisions of this AD, except 

for AMOCs that change the inspection 

frequency. 

(k) Related Information 

(1) For more information about this AD, 

contact Rebel Nichols, Aerospace Engineer, 

Propulsion Branch, ANM–140S, Seattle 

Aircraft Certification Office (ACO), FAA, 

1601 Lind Avenue SW., Renton, WA 98057– 

3356; phone: 425–917–6509; fax: 425–917– 

6590; email: Rebel.Nichols@faa.gov. 

(2) For Boeing service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data & 

Services Management, P. O. Box 3707, MC 

2H–65, Seattle, WA 98124–2207; telephone 

206–544–5000, extension 1; fax 206–766– 

5680; Internet https:// 

www.myboeingfleet.com. 

(l) 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. 

(3) The following service information was 

approved for IBR on October 1, 2001 (66 FR 

44954, August 27, 2001). 

(i) Boeing Service Bulletin A3500, Revision 

1, dated April 26, 2001. 

(ii) Reserved. 

(4) For Boeing service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data & 

Services Management, P. O. Box 3707, MC 

2H–65, Seattle, WA 98124–2207; telephone 

206–544–5000, extension 1; fax 206–766– 

5680; Internet https:// 

www.myboeingfleet.com. 

(5) You may review copies of the 

referenced service information at the FAA, 

Transport Airplane Directorate, 1601 Lind 

Avenue SW., Renton, WA. For information 

on the availability of this material at the 

FAA, call 425–227–1221. 

(6) 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/ibrlocations.html. 

Issued in Renton, Washington on February 

6, 2013. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–03267 Filed 2–13–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1055; Directorate 

Identifier 2012–NE–33–AD; Amendment 39– 

17351; AD 2013–03–17] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

Deutschland Ltd & Co KG Turbofan 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Rolls-Royce Deutschland Ltd & Co KG 

(RRD) BR700–710A1–10 and BR700– 

710A2–20 turbofan engines, and certain 

BR700–710C4–11 model engines. This 

AD was prompted by RRD performing 

an evaluation that determined that 

certain high-pressure turbine (HPT) 

stage 1 and stage 2 discs from a specific 

supplier may contain steel inclusions 

that may cause the discs to fail before 

they reach their current life limits. This 

AD requires reducing the life limits for 

certain HPT stage 1 and stage 2 discs. 

We are issuing this AD to prevent 

failure of the HPT stage 1 and stage 2 

discs, which could result in 

uncontained failure of the engine and 

damage to the airplane. 

DATES: This AD becomes effective 

March 21, 2013. 

ADDRESSES: The Docket Operations 

office is located at Docket Management 

Facility, U.S. Department of 

Transportation, 1200 New Jersey 

Avenue SE., West Building Ground 

Floor, Room W12–140, Washington, DC 

20590–0001. 

FOR FURTHER INFORMATION CONTACT: 

Robert Morlath, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7154; fax: 781–238– 

7199; email: robert.c.morlath@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 was published in the Federal 

Register on November 16, 2012 (77 FR 

68714). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The Mandatory Continuing 

Airworthiness Information (MCAI) 

states: 

The results of a recent quality review of 

high pressure turbine (HPT) stage 1 and stage 

2 discs identified potential for steel 

inclusions in some production scale parts. 

Further investigation concluded that all 

affected parts were manufactured by Udimet 

720I and melted by a certain supplier. 

Subsequent evaluation concluded that the 

affected parts life limitation values declared 

in the engine Time Limits Manual cannot be 

supported for discs with potential steel 

inclusion. 

This condition, if not corrected, could lead 

to an uncontained HPT disc failure, 

potentially resulting in damage to, and/or 

reduced control of the aeroplane. 

The FAA has further determined that 

the risk to the engine is increased by 

installing an HPT stage 1 disc and an 

HPT stage 2 disc from the affected 

population, on the same engine. 

Therefore the FAA is prohibiting the 

installation of an HPT stage 1 and HPT 

stage 2 discs from the affected 

population in the same engine. You may 

obtain further information by examining 

the MCAI in the AD docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

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