This section of the FEDERAL REGISTER

contains notices to the public of the proposed

issuance of rules and regulations. The

purpose of these notices is to give interested

persons an opportunity to participate in the

rule making prior to the adoption of the final

rules.

Proposed Rules Federal Register

61731 

Vol. 77, No. 197 

Thursday, October 11, 2012 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1069; Directorate 

Identifier 2012–NM–044–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede an 

existing airworthiness directive (AD) 

that applies to all The Boeing Company 

Model 727 airplanes. The existing AD 

currently requires repetitive inspections 

of the in-tank fuel boost pump wiring to 

detect chafing of the wire insulation, 

evidence of electrical arcing, or arcthrough of the conduit wall, and 

applicable corrective action; and 

installation of sleeving over the in-tank 

fuel boost pump wires. The existing AD 

also requires repetitive inspections for 

damage of a certain electrical wire and 

sleeve, and arcing damage of the 

conduit and signs of fuel leakage into 

the conduit; applicable investigative 

and corrective actions; and repetitive 

engine fuel suction feed operational 

tests. Since we issued that AD, we 

received a report of damage found to the 

sleeve, jacket, and insulation on an 

electrical wire during a repetitive 

inspection. This proposed AD would 

require replacement of the wire bundles 

for the wing and center fuel boost 

pumps with new, improved wire 

bundles, installation of convoluted 

liners, and related investigative and 

corrective actions if necessary. This 

proposed AD would also require 

replacement of the fuel quantity 

indicating system (FQIS) wires with 

new, improved wires; a low-frequency 

eddy current inspection for cracking; 

and repair if necessary. This proposed 

AD would also require revising the 

maintenance program to incorporate 

changes to the airworthiness limitations 

section. We are proposing this AD to 

detect and correct chafing of the fuel 

boost pump electrical wiring and 

leakage of fuel into the conduit, and to 

prevent electrical arcing between the 

wiring and the surrounding conduit, 

which could result in arc-through of the 

conduit, and consequent fire or 

explosion of the fuel tank. 

DATES: We must receive comments on 

this proposed AD by November 26, 

2012. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, 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: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed 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 proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Rebel Nichols, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6509; fax: 

425–917–6590; email: rebel.nichols@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2012–1069; Directorate Identifier 

2012–NM–044–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed 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 proposed AD. 

Discussion 

On May 1, 2007, we issued AD 2007– 

11–08, Amendment 39–15065 (72 FR 

28594, May 22, 2007), for all The Boeing 

Company Model 727, 727C, 727–100, 

727–100C, 727–200, and 727–200F 

series airplanes. That AD requires 

repetitive inspections of the in-tank fuel 

boost pump wiring to detect chafing of 

the wire insulation, evidence of 

electrical arcing, or arc-through of the 

conduit wall, and applicable corrective 

action; and installation of sleeving over 

the in-tank fuel boost pump wires as a 

method to protect the wiring from 

chafing. That AD also requires repetitive 

inspections for damage of the electrical 

wire and sleeve that run to the fuel 

boost pump through a conduit in the 

fuel tank, and arcing damage of the 

conduit and signs of fuel leakage into 

the conduit; applicable investigative 

and corrective actions; repetitive engine 

fuel suction feed operational tests; an 

engine fuel suction feed operational test; 

related investigative and corrective 

actions, as applicable; and sending 


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inspection results and damaged parts to 

the manufacturer. 

Actions Since Existing AD (72 FR 

28594, May 22, 2007) Was Issued 

In the preamble to AD 2007–11–08, 

Amendment 39–15065 (72 FR 28594, 

May 22, 2007), the FAA indicated that 

the actions required by that AD were 

considered ‘‘interim action’’ and that 

further rulemaking action was being 

considered. The FAA now has 

determined that further rulemaking 

action is indeed necessary, and this 

proposed AD follows from that 

determination. 

Further, since we issued AD 2007– 

11–08, Amendment 39–15065 (72 FR 

28594, May 22, 2007), we received a 

report of damage found to the sleeve, 

jacket, and insulation on an electrical 

wire during a repetitive inspection 

approximately 21,000 flight hours after 

installation of the sleeve. (The 

inspection interval in AD 2007–11–08 is 

30,000 flight hours.) The sleeve and 

jacket were worn through, exposing the 

insulation on the electrical wire inside 

the jacket. The actions developed by the 

manufacturer eliminate the possibility 

of wiring damage during reinstallation 

following the repetitive inspections. 

Relevant Service Information 

We reviewed Boeing Alert Service 

Bulletin 727–28A0133, dated October 5, 

2011. This service bulletin describes 

procedures for replacing wire bundles 

for the wing and center fuel boost 

pumps, installing convoluted liners, and 

related investigative and corrective 

actions. This service bulletin specifies 

that doing these actions eliminates the 

need for the inspections specified in 

Boeing Alert Service Bulletin 727– 

28A0132, dated February 22, 2007 

(which is referenced as the appropriate 

source of service information for 

inspections specified in AD 2007–11– 

08, Amendment 39–15065 (72 FR 

28594, May 22, 2007)). Replacing the 

wire bundles and installing the 

convoluted liners includes: 

• Installing new ground brackets, 

removing fuel boost pumps from the 

fuel boost pump housing, and removing 

wire bundles and sleeves. 

• Removing or stowing fuel boost 

pump wire bundles, installing new 

convoluted liners and new wire bundles 

in the fuel boost pump conduits. 

• Routing new wire bundles. 

• Installing fuel boost pumps and 

making changes to the wire bundles. 

• Installing the ground stud assembly 

for wire bundles. 

Related investigative actions include 

testing the fuel tank conduits for leaks 

and testing the fuel boost pumps. 

Corrective actions include repairing or 

replacing the fuel tank conduit. 

Boeing Alert Service Bulletin 727– 

28A0133, dated October 5, 2011, 

specifies prior or concurrent 

accomplishment of the actions specified 

in Boeing Service Bulletin 727–28– 

0131, dated August 18, 2010, for the 

following actions: 

• Replacing the FQIS wires with new 

wires, which includes: Installing new 

ground brackets in the left and right 

wing, a new disconnect bracket in the 

cargo compartment, and a new tie plate 

in the cargo compartment; making and 

installing new doublers in the left and 

right wing; installing new standoffs in 

the left and right wing; drilling new 

holes or ground holes in left and right 

wing; changing the wire bundles; 

making changes to wire bundle routes; 

and making changes to wire bundles 

and assembling wire bundle overbraids. 

• Doing a low-frequency eddy current 

(LFEC) inspection for cracks in certain 

locations of the fuselage skin, and repair 

if necessary, in accordance with Boeing 

Service Bulletin 727–28–0131, dated 

August 18, 2010. 

Airworthiness Limitation Instruction 

(ALI) Task 28–AWL–20, ‘‘Fuel Boost 

Pump Wires in Conduit Installation—In 

Fuel Tank;’’ and Critical Design 

Configuration Control Limitation 

(CDCCL) Task 28–AWL–21, ‘‘Fuel Boost 

Pump Wires in Conduit Installation—In 

Fuel Tank;’’ of Section 9 of Boeing 727– 

100/200 Airworthiness Limitations 

(AWLs), D6–8766–AWL, Revision 

August 2010, provide maintenance 

instructions for the wiring changes and 

replace the requirements of CDCCL Task 

28–AWL–14 of Section 9 of Boeing 727– 

100/200 Airworthiness Limitations 

(AWLs), D6–8766–AWL. 

FAA’s Determination 

We are proposing 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 the same 

type design. 

Proposed AD Requirements 

This proposed AD would retain 

certain requirements of AD 2007–11–08, 

Amendment 39–15065 (72 FR 28594, 

May 22, 2007). This proposed AD would 

also require accomplishing the actions 

specified in the service information 

described previously, except as 

provided under ‘‘Differences Between 

the AD and the Service Information.’’ 

Differences Between the Proposed AD 

and the Service Information 

Although Boeing Alert Service 

Bulletin 727–28A0133, dated October 5, 

2011, specifies that operators may 

contact the manufacturer for disposition 

of certain repair conditions, this 

proposed AD would require operators to 

repair those conditions using a method 

approved by the FAA. 

Change to Existing AD 

This proposed AD would remove the 

reporting requirements of paragraph (m) 

of AD 2007–11–08, Amendment 39– 

15065 (72 FR 28594, May 22, 2007). The 

inspection report requirement gathered 

sufficient information for the 

manufacturer to develop corrective 

actions. 

This proposed AD would retain 

certain requirements of AD 2007–11–08, 

Amendment 39–15065 (72 FR 28594, 

May 22, 2007). Since AD 2007–11–08 

was issued, the AD format has been 

revised, and certain paragraphs have 

been rearranged. Also, certain notes 

have been re-designated as paragraphs. 

As a result, the corresponding paragraph 

identifiers have changed in this 

proposed AD, as listed in the following 

table: 

REVISED PARAGRAPH IDENTIFIERS

Requirement in AD 

2007–11–08, amendment 39–15065 (72 

FR 28594, May 22, 

2007) 

Corresponding 

requirement in this 

proposed AD 

paragraph (f) paragraph (g)(1) 

paragraph (g) paragraph (g)(2) 

paragraph (h) paragraph (g)(3) 

paragraph (i) paragraph (h) 

paragraph (j) paragraph (i) 

paragraph (k) paragraph (j) 

paragraph (l) paragraph (k) 

Costs of Compliance 

We estimate that this proposed AD 

affects 569 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 


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Federal Register / Vol. 77, No. 197 / Thursday, October 11, 2012 / Proposed Rules 61733 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Number of 

U.S. airplanes 

Cost on U.S. 

operators 

Inspection, test, and corrective actions [retained actions from existing AD 2007-11-08, Amendment 39-15065 (72 FR 28594, 

May 22, 2007)].

10 work-hours × $85 per hour = 

$850.

$0 ..................... $850 ................. 260 $221,000. 

Replacement [proposed action] .... 185 work-hours × $85 per hour = 

$15,725.

$28,771 ............ $44,496 ............ 569 $25,318,224. 

Revise Maintenance Program 

[proposed action].

1 work-hour × $85 per hour = 

$85.

$0 ..................... $85 ................... 569 $48,365. 

Concurrent FQIS wire replacement [proposed action].Up to 248 work-hours × $85 per 

hour = $21,080.

Up to $34,865 .. Up to $55,945 .. 569 Up to 

$31,832,705. 

Concurrent low frequency eddy 

current (LFEC) inspection [proposed action].

2 work-hours × $85 per hour = 

$170.

$0 ..................... $170 ................. 569 $96,730. 

We have received no definitive data 

that would enable us to provide a cost 

estimate for the on-condition actions 

specified in this proposed 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 

proposed AD would not have federalism 

implications under Executive Order 

13132. This proposed AD would 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 the proposed regulation: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

the 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. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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) 

2007–11–08, Amendment 39–15065 (72 

FR 28594, May 22, 2007), and adding 

the following new AD: 

The Boeing Company: Docket No. FAA– 

2012–1069; Directorate Identifier 2012– 

NM–044–AD. 

(a) Comments Due Date 

The FAA must receive comments on this 

AD action by November 26, 2012. 

(b) Affected ADs 

This AD supersedes AD 2007–11–08, 

Amendment 39–15065 (72 FR 28594, May 22, 

2007), which superseded AD 99–12–52, 

Amendment 39–11199 (64 FR 33394, June 

23, 1999). 

(c) Applicability 

(1) This AD applies to all Boeing Model 

727, 727C, 727–100, 727–100C, 727–200, and 

727–200F series airplanes, certificated in any 

category. 

(2) This AD requires revisions to certain 

operator maintenance documents to include 

new actions (e.g., inspections) and/or Critical 

Design Configuration Control Limitations 

(CDCCLs). Compliance with these actions 

and/or CDCCLs is required by 14 CFR 

91.403(c). For airplanes that have been 

previously modified, altered, or repaired in 

the areas addressed by this AD, the operator 

may not be able to accomplish the actions 

described in the revisions. In this situation, 

to comply with 14 CFR 91.403(c), the 

operator must request approval for an 

alternative method of compliance according 

to paragraph (p) of this AD. The request 

should include a description of changes to 

the required actions that will ensure the 

continued operational safety of the airplane. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 28, Fuel. 

(e) Unsafe Condition 

This AD was prompted by a report of 

damage found to the sleeve, jacket, and 

insulation on an electrical wire during a 

repetitive inspection. We are issuing this AD 

to detect and correct chafing of the fuel boost 

pump electrical wiring and leakage of fuel 

into the conduit, and to prevent electrical 

arcing between the wiring and the 

surrounding conduit, which could result in 

arc-through of the conduit, and consequent 

fire or explosion of the fuel tank. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Compliance Times 

This paragraph restates the requirements of 

paragraphs (f), (g), and (h) of AD 2007–11– 

08, Amendment 39–15065 (72 FR 28594, May 

22, 2007). 

(1) For airplanes with 50,000 or more total 

flight hours as of June 28, 1999 (the effective 

date of AD 99–12–52, Amendment 39–11199 

(64 FR 33394, June 23, 1999)): Within 20 

days after June 28, 1999, accomplish the 

requirements of paragraph (h) of this AD. 

(2) For airplanes with less than 50,000 total 

flight hours, but more than 30,000 total flight 


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hours, as of June 28, 1999 (the effective date 

of AD 99–12–52, Amendment 39–11199 (64 

FR 33394, June 23, 1999)): Within 30 days 

after June 28, 1999, accomplish the 

requirements of paragraph (h) of this AD. 

(3) For airplanes with 30,000 total flight 

hours or less as of June 28, 1999 (the effective 

date of AD 99–12–52, Amendment 39–11199 

(64 FR 33394, June 23, 1999)): Within 90 

days after June 28, 1999, accomplish the 

requirements of paragraph (h) of this AD. 

(h) Retained Detailed Inspection, Corrective 

Action, and Installation 

This paragraph restates the requirements of 

paragraph (i) of AD 2007–11–08, Amendment 

39–15065 (72 FR 28594, May 22, 2007). 

(1) Perform a detailed inspection of the intank fuel boost pump wire bundles, and 

applicable corrective actions; and, except as 

provided by paragraph (i) of this AD, install 

sleeving over the wire bundles; in accordance 

with Boeing Alert Service Bulletin 727– 

28A0126, dated May 24, 1999; Boeing 

Service Bulletin 727–28A0126, Revision 1, 

dated May 18, 2000; or Boeing Alert Service 

Bulletin 727–28A0132, dated February 22, 

2007. 

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

inspection is: ‘‘An intensive examination of 

a specific item, installation, or assembly to 

detect damage, failure, or irregularity. 

Available lighting is normally supplemented 

with a direct source of good lighting at an 

intensity deemed appropriate. Inspection 

aids such as mirror, magnifying lenses, etc., 

may be necessary. Surface cleaning and 

elaborate procedures may be required.’’ 

(i) Retained Installation: Possible Deferral 

This paragraph restates the optional 

actions of paragraph (j) of AD 2007–11–08, 

Amendment 39–15065 (72 FR 28594, May 22, 

2007). Installation of sleeving over the wire 

bundles, as required by paragraph (h) of this 

AD, may be deferred if, within 18 months or 

6,000 flight hours, whichever occurs first, 

after accomplishment of the inspection and 

applicable corrective actions required by 

paragraph (h) of this AD, the following 

actions are accomplished: Perform a detailed 

inspection of the in-tank fuel boost pump 

wire bundles, and applicable corrective 

actions; and install sleeving over the wire 

bundles; in accordance with Boeing Alert 

Service Bulletin 727–28A0126, dated May 

24, 1999; Boeing Service Bulletin 727– 

28A0126, Revision 1, dated May 18, 2000; or 

Boeing Alert Service Bulletin 727–28A0132, 

dated February 22, 2007. 

(j) Retained Repetitive Inspections and 

Corrective Actions 

This paragraph restates the requirements of 

paragraph (k) of AD 2007–11–08, 

Amendment 39–15065 (72 FR 28594, May 22, 

2007). Repeat the detailed inspection and 

applicable corrective actions required by 

paragraphs (h) and (i) of this AD, as 

applicable, at intervals not to exceed 30,000 

flight hours, until the initial inspection, 

applicable corrective actions, and engine fuel 

suction feed operational test required by 

paragraph (k) of this AD have been done. 

(k) Retained Inspection, Test, and Related 

Investigative and Corrective Actions 

This paragraph restates the requirements of 

paragraph (l) of AD 2007–11–08, Amendment 

39–15065 (72 FR 28594, May 22, 2007). For 

all airplanes: Within 120 days after June 6, 

2007 (the effective date of AD 2007–11–08), 

or 5,000 flight hours after the last inspection 

or corrective action done before June 6, 2007, 

as required by paragraph (h), (i), or (j), as 

applicable, of this AD, whichever occurs 

later, do a detailed inspection for damage of 

the sleeve and electrical wire of the fuel 

boost pump, and do an engine fuel suction 

feed operational test; and, before further 

flight, do related investigative and corrective 

actions, as applicable; by doing all applicable 

actions in and in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 727–28A0132, dated 

February 22, 2007. Repeat the detailed 

inspection and engine fuel suction feed 

operational test thereafter at intervals not to 

exceed 15,000 flight cycles. Accomplishment 

of the initial inspection, applicable corrective 

actions, and engine fuel suction feed 

operational test of this paragraph terminates 

the requirements of paragraphs (h), (i), and (j) 

of this AD. 

(l) New Installation 

Within 60 months after the effective date 

of this AD: Install new shielded wire bundles 

in convoluted liners in the wing and center 

fuel tank conduits and do all applicable 

related investigative and corrective actions, 

in accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

727–28A0133, dated October 5, 2011. Related 

investigative and corrective actions must be 

done before further flight. Doing the actions 

in paragraphs (l) and (m) of this AD 

terminates the requirements of paragraphs 

(g), (h), (i), (j), and (k) of this AD. 

(m) New Concurrent Requirement 

Before or concurrently with accomplishing 

the requirements of paragraph (l) of this AD, 

replace the fuel quantity indicating system 

(FQIS) wire bundles and do a low frequency 

eddy current inspection for cracking, in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 727– 

28–0131, dated August 18, 2010. If any 

cracking is found during the inspection, 

before further flight, repair using a method 

approved in accordance with the procedures 

specified in paragraph (p) of this AD. 

(n) New Maintenance Program Revision 

Within 60 days after the effective date of 

this AD: Revise the maintenance program to 

incorporate Airworthiness Limitation 

Instruction (ALI) Task 28–AWL–20, ‘‘Fuel 

Boost Pump Wires in Conduit Installation— 

In Fuel Tank;’’ and CDCCL Task 28–AWL– 

21, ‘‘Fuel Boost Pump Wires in Conduit 

Installation—In Fuel Tank,’’ of Section 9 of 

Boeing 727–100/200 Airworthiness 

Limitations (AWLs), D6–8766–AWL, 

Revision August 2010. The initial 

compliance time for the inspections is within 

60 months after the effective date of this AD. 

(o) No Alternative Actions, Intervals, and/or 

CDCCLs 

After accomplishing the revision required 

by paragraph (n) of this AD, no alternative 

actions (e.g., inspections), intervals, and/or 

CDCCLs may be used unless the actions, 

intervals, and/or CDCCLs are approved as an 

alternative method of compliance (AMOC) in 

accordance with the procedures specified in 

paragraph (p) of this AD. 

(p) 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) AMOCs approved previously in 

accordance with AD 2007–11–08, 

Amendment 39–15065 (72 FR 28594, May 22, 

2007), are approved as AMOCs for the 

corresponding provisions of this AD. 

(q) Related Information 

(1) For more information about this AD, 

contact Rebel Nichols, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6509; fax: 425–917–6590; 

email: rebel.nichols@faa.gov. 

(2) 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. 

Issued in Renton, Washington, on 

September 28, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–24954 Filed 10–10–12; 8:45 am] 

BILLING CODE 4910–13–P 


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