Federal Register / Vol. 78, No. 156 / Tuesday, August 13, 2013 / Proposed Rules 49217 

Maintenance, dated January 8, 2008; or 

within 4 months after the effective date of 

this AD; whichever occurs later. 

(n) New Limitation: No Alternative Actions 

or Intervals 

After accomplishing the revision required 

by paragraph (m) of this AD, no alternative 

actions (e.g., inspections) or intervals, may be 

used unless the actions or intervals are 

approved as an alternative method of 

compliance (AMOC) in accordance with the 

procedures specified in paragraph (o) of this 

AD. 

(o) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, 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 International Branch, send it to ATTN: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1405; fax 425–227–1149. 

Information may be emailed to: 9-ANM-116- 

AMOC-REQUESTS@faa.gov. 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. The AMOC approval letter 

must specifically reference this AD. AMOCs 

approved previously in accordance with AD 

2011–14–06, Amendment 39–16741 (76 FR 

42024, July 18, 2011), are approved as 

AMOCs for the corresponding actions 

specified in this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(p) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information European 

Aviation Safety Agency (EASA) 

Airworthiness Directive 2012–0008, dated 

January 16, 2012, and the service information 

specified in paragraphs (p)(1)(i) through 

(p)(1)(viii) of this AD, for related information. 

(i) Airbus A318/A319/A320/A321 ALS Part 

1—Safe Life Airworthiness Limitation Items, 

Revision 02, dated May 13, 2011. 

(ii) Airbus A318/A319/A320/A321 ALS 

Part 1—Safe Life Airworthiness Limitation 

Items, dated February 28, 2006. 

(iii) Airbus A318/A319/A320/A321 ALS 

Part 4—Ageing Systems Maintenance, dated 

January 8, 2008. 

(iv) Airbus A318/A319/A320/A321 

Airworthiness Limitation Items, Document 

AI/SE–M4/95A.0252/96, Issue 7, dated 

December 2005. 

(v) Airbus A318/A319/A320/A321 

Airworthiness Limitation Items, Document 

AI/SE–M4/95A.0252/96, Issue 08, dated 

March 2006. 

(vi) Airbus A318/A319/A320/A321 

Airworthiness Limitation Items, Document 

AI/SE–M4/95A.0252/96, Issue 09, dated 

November 2006. 

(vii) Airbus A318/A319/A320/A321 

Airworthiness Limitation Items, Document 

AI/SE–M4/95A.0252/96, Issue 10, dated 

October 2009. 

(viii) Airbus A318/A319/A320/A321 

Airworthiness Limitation Items, Document 

AI/SE–M4/95A.0252/96, Issue 11, dated 

September 2010. 

(2) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EIAS, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 61 

93 44 51; email account.airwortheas@airbus.com; Internet http:// 

www.airbus.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 August 

2, 2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–19528 Filed 8–12–13; 8:45 am] 

BILLING CODE 4910–13–P 

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: Supplemental notice of 

proposed rulemaking (NPRM); 

reopening of comment period. 

SUMMARY: We are revising an earlier 

proposed airworthiness directive (AD), 

for all The Boeing Company Model 727 

airplanes, which proposed to supersede 

an existing AD. That NPRM proposed to 

retain repetitive inspections of the intank fuel boost pump wiring, 

installation of sleeving over the in-tank 

fuel boost pump wires, repetitive 

inspections of a certain electrical wire, 

sleeve, and conduit, and applicable 

investigative and corrective actions; and 

repetitive engine fuel suction feed 

operational tests. That NPRM proposed 

to also require replacement of the wire 

bundles for the wing and center fuel 

boost pumps, installation of convoluted 

liners, and related investigative and 

corrective actions if necessary. That 

NPRM also proposed to require 

replacement of the fuel quantity 

indicating system (FQIS) wires; a lowfrequency eddy current inspection for 

cracking; and repair if necessary. That 

NPRM also proposed to require revising 

the maintenance program to incorporate 

changes to the airworthiness limitations 

section. That NPRM was prompted by a 

report of damage found to the sleeve, 

jacket, and insulation on an electrical 

wire during a repetitive inspection. This 

action revises that NPRM by revising 

certain compliance times, specifying a 

terminating action, and adding a 

proposed requirement to incorporate 

another change to the airworthiness 

limitations section. We are proposing 

this supplemental NPRM to prevent 

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 arcthrough of the conduit, and consequent 

fire or explosion of the fuel tank. Since 

these actions impose an additional 

burden over that proposed in the NPRM, 

we are reopening the comment period to 

allow the public the chance to comment 

on these proposed changes. 

DATES: We must receive comments on 

this supplemental NPRM by September 

27, 2013. 

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: 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, 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 


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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 

We issued an NPRM to amend 14 CFR 

part 39 to include an AD that would 

apply to to all Boeing Model 727, 727C, 

727–100, 727–100C, 727–200, and 727– 

200F series airplanes, certificated in any 

category. That NPRM published in the 

Federal Register on October 11, 2012 

(77 FR 61731). That NPRM proposed to 

retain repetitive inspections of the intank 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. That 

NPRM also proposed to retain 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. That NPRM proposed 

to 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. That 

NPRM also proposed to require 

replacement of the FQIS wires with 

new, improved wires; a low-frequency 

eddy current inspection for cracking; 

and repair if necessary. That NPRM also 

proposed to require revising the 

maintenance program to incorporate 

changes to the airworthiness limitations 

section. 

Actions Since Previous NPRM (77 FR 

61731, October 11, 2012) Was Issued 

Since we issued the previous NPRM 

(77 FR 61731, October 11, 2012), we 

have determined that additional 

limitations are necessary and that the 

initial compliance time for one task 

must be reduced. The preamble to AD 

2007–11–08, Amendment 39–15065 (72 

FR 28594, May 22, 2007) explains that 

we consider the requirements ‘‘interim 

action’’ and were considering further 

rulemaking. We now have determined 

that further rulemaking is indeed 

necessary, and this proposed AD 

follows from that determination. 

Comments 

We gave the public the opportunity to 

comment on the NPRM (77 FR 61731, 

October 11, 2012). The following 

presents the comments received on the 

NPRM and the FAA’s response to each 

comment. 

Request To Add Airworthiness 

Limitations 

Boeing requested that we add ALI 

Task 28–AWL–18, ‘‘Fuel Quantity 

Indicating System (FQIS)—Out-Tank 

Wiring Lightning Shield to Ground 

Termination,’’ and Critical Design 

Configuration Control Limitation 

(CDCCL) Task 28–AWL–19, ‘‘Fuel 

Quantity Indicating System (FQIS)— 

Out-Tank Wiring Lightning Shield to 

Ground Termination’’ to the original 

NPRM (77 FR 61731, October 11, 2012). 

We agree with the request. We have 

added new paragraph (n)(1) in this 

supplemental NPRM to require revising 

the maintenance program to include 

both tasks. These AWL’s are necessary 

after accomplishing the actions 

specified in Boeing Alert Service 

Bulletin 727–28A013, dated August 18, 

2010, which is proposed in paragraph 

(m) of this supplemental NPRM. 

Request for Correction 

Boeing requested that we correct the 

Relevant Service Information section 

and paragraph (n) of the NPRM (77 FR 

61731, October 11, 2012) to refer to 

Section B rather than Section 9 of 

Boeing 727–100/200 Airworthiness 

Limitations (AWLs), D6–8766–AWL, 

Revision August 2010. Boeing stated 

that there is no section 9 in that 

document. 

We agree with the request. Although 

the Relevant Service Information is not 

repeated in this supplemental NPRM, 

we have made the correction to new 

paragraph (n)(2) of this supplemental 

NPRM (which was paragraph (n) of the 

previous NPRM (77 FR 61731, October 

11, 2012)). 

Change to Compliance Time 

Paragraph (n) of the previous NPRM 

(77 FR 61731, October 11, 2012) 

specified a compliance time of 60 

months after the effective date of the AD 

for accomplishing the initial task for 

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 

B of Boeing 727–100/200 Airworthiness 

Limitations (AWLs), D6–8766–AWL, 

Revision August 2010. We have added 

paragraph (n)(2) to this supplemental 

NPRM to change the compliance time 

for accomplishing the initial task to 

within 72 months after accomplishing 

the actions specified in Boeing Service 

Bulletin 727–28A0133, dated October 5, 

2011. 

FAA’s Determination 

We are proposing this supplemental 

NPRM 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. Certain changes described above 

expand the scope of the previous NPRM 

(77 FR 61731, October 11, 2012). As a 

result, we have determined that it is 

necessary to reopen the comment period 

to provide additional opportunity for 

the public to comment on this 

supplemental NPRM. 

Proposed Requirements of the 

Supplemental NPRM 

This supplemental NPRM would 

require accomplishing the actions 


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specified in the service information 

described previously, except as 

discussed under ‘‘Differences Between 

the Supplemental NPRM and the 

Service Information.’’ 

Differences Between the Supplemental 

NPRM 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 in accordance with the 

procedures specified in paragraph (p) of 

this AD. 

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: 

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 proposed 

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 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 this 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 adding 

the following new airworthiness 

directive (AD): 

The Boeing Company: Docket No. FAA– 

2012–1069; Directorate Identifier 2012– 

NM–044–AD. 

(a) Comments Due Date 

We must receive comments by September 

27, 2013. 

(b) Affected ADs 

This AD supersedes AD 2007–11–08, 

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

2007). 

(c) Applicability 

(1) This AD applies to all The Boeing 

Company 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. 


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(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 prevent 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 

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 

specified 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 

(1) Within 60 days after the effective date 

of this AD: Revise the maintenance program 

to incorporate Airworthiness Limitation 

Instruction (ALI) Task 28–AWL–18, ‘‘Fuel 

Quantity Indicating System (FQIS)—OutTank Wiring Lightning Shield to Ground 

Termination’’; and CDCCL Task 28–AWL–19, 

‘‘Fuel Quantity Indicating System (FQIS)— 

Out-Tank Wiring Lightning Shield to Ground 

Termination,’’ of Section B of Boeing 727– 

100/200 Airworthiness Limitations (AWLs), 

D6–8766–AWL, Revision August 2010. The 

initial compliance time for the inspections is 

within 120 months after accomplishing the 

actions required by paragraph (m) of this AD. 

(2) 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 B of 

Boeing 727–100/200 Airworthiness 

Limitations (AWLs), D6–8766–AWL, 

Revision August 2010. The initial 

compliance time for the inspections is within 

72 months after accomplishing the actions 

required by paragraph (l) of this AD. 

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

CDCCLs 

After accomplishing the revisions required 

by paragraphs (n)(1) and (n)(2) 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. 


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Federal Register / Vol. 78, No. 156 / Tuesday, August 13, 2013 / Proposed Rules 49221 

(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. 

(4) 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 August 

2, 2013. 

Ross Landes, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–19527 Filed 8–12–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0724; Directorate 

Identifier 99–CE–013–AD] 

RIN 2120–AA64 

Airworthiness Directives; Piper 

Aircraft, Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to revise 

airworthiness directive (AD) 99–26–19 

that applies to certain The New Piper 

Aircraft, Inc. Model J–2 airplanes 

equipped with wing lift struts. AD 99– 

26–19 currently requires repetitively 

inspecting the wing lift struts for dents 

and corrosion; repetitively inspecting 

the wing lift strut forks for cracks; 

replacing any dented or corroded wing 

lift strut; replacing any cracked wing lift 

strut fork; and repetitively replacing the 

wing lift strut forks at specified times 

for certain airplanes. AD 99–26–19 also 

currently requires incorporating a ‘‘NO 

STEP’’ placard on the wing lift strut. 

Since we issued AD 99–26–19, we have 

been informed that paragraph (c) is 

being misinterpreted and causing 

confusion. This proposed AD would 

clarify the intent of the language 

currently in paragraph (c) of AD 99–26– 

19 and would retain all other 

requirements of AD 99–26–19. We are 

proposing this AD to correct the unsafe 

condition on these products. 

DATES: We must receive comments on 

this proposed AD by September 27, 

2013. 

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 Piper 

Aircraft, Inc., Customer Services, 2926 

Piper Drive, Vero Beach, Florida 32960; 

telephone: (772) 567–4361; Internet: 

www.piper.com. Information about the 

Jensen Aircraft STCs may be obtained 

from F. Atlee Dodge, Aircraft Services, 

LLC, 6672 Wes Way, Anchorage, Alaska 

99518–0409, Internet: 

www.fadodge.com. You may review 

copies of the referenced service 

information at the FAA, Small Airplane 

Directorate, 901 Locust, Kansas City, 

Missouri 64106. For information on the 

availability of this material at the FAA, 

call (816) 329–4148. 

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: 

Gregory ‘‘Keith’’ Noles, Aerospace 

Engineer, FAA, Atlanta Aircraft 

Certification Office, 1701 Columbia 

Avenue, College Park, Georgia 30337; 

phone: (404) 474–5551; fax: (404) 474– 

5606; email: gregory.noles@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–2013–0724; Directorate Identifier 

99–CE–013–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 December 16, 1999, we issued AD 

99–26–19, Amendment 39–11479 (64 

FR 72524, December 28, 1999), (‘‘AD 

99–26–19’’), for certain The New Piper 

Aircraft, Inc. (currently Piper Aircraft, 

Inc.) J–2 series airplanes equipped with 

wing lift struts. We issued AD 99–26– 

19 because J–2 series airplanes were 

inadvertently omitted from the 

applicability of AD 99–01–05, 

Amendment 39–10972 (63 FR 72132, 

December 31, 1998, (‘‘99–01–05’’). 

AD 99–01–05 was issued to supersede 

AD 93–10–06, Amendment 39–8586 (58 

FR 29965, May 25, 1993), which 

previously included J–2 series airplanes 

in the Applicability section, in order to 

include a terminating action for 

repetitively inspecting and replacing the 

wing lift struts and the wing lift strut 

forks. 

We issued both ADs to detect and 

correct corrosion and cracking on the 

front and rear wing lift struts and forks, 

which could cause the wing lift strut to 

fail. This failure could result in the wing 

separating from the airplane. 


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