Federal Register / Vol. 81, No. 45 / Tuesday, March 8, 2016 / Proposed Rules 12041 

effective date of this AD, install new engine 

fuel spar motor operated valve (MOV) 

actuators having part number (P/N) 

MA30A1017, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 777–28A0034, Revision 3, 

dated September 25, 2015. 

(2) For airplanes having AIMS 2, 

Blockpoint Version 16 or earlier installed: 

Within 24 months after the effective date of 

this AD, do the actions in paragraph (g)(2)(i) 

or (g)(2)(ii) of this AD. 

(i) Install new engine fuel spar MOV 

actuators having P/N MA30A1017, in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 777– 

28A0034, Revision 3, dated September 25, 

2015. 

(ii) Install AIMS 2, Blockpoint Version 17 

or later, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 777–31–0227, Revision 1, 

dated August 12, 2015. 

(h) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraph (g)(2)(ii) of this AD, if 

those actions were performed before the 

effective date of this AD using Boeing Special 

Attention Service Bulletin 777–31–0227, 

dated November 7, 2014, which is not 

incorporated by reference in this AD. 

(i) 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 

paragraph (j)(1) of this AD. Information may 

be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@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, 

modification, or alteration 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. To be 

approved, the repair method, modification 

deviation, or alteration deviation must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) For service information that contains 

steps that are labeled as Required for 

Compliance (RC), the provisions of 

paragraphs (i)(4)(i) and (i)(4)(ii) of this AD 

apply. 

(i) The steps labeled as RC, including 

substeps under an RC step and any figures 

identified in an RC step, must be done to 

comply with the AD. An AMOC is required 

for any deviations to RC steps, including 

substeps and identified figures. 

(ii) Steps not labeled as RC may be 

deviated from using accepted methods in 

accordance with the operator’s maintenance 

or inspection program without obtaining 

approval of an AMOC, provided the RC steps, 

including substeps and identified figures, can 

still be done as specified, and the airplane 

can be put back in an airworthy condition 

(j) Related Information 

(1) For more information about this AD, 

contact David Lee, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6497; fax: 425–917–6590; 

email: david.a.lee@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 view this 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 February 

25, 2016. 

Dionne Palermo, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–04682 Filed 3–7–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0935; Directorate 

Identifier 2014–NM–243–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Supplemental notice of 

proposed rulemaking (SNPRM); 

reopening of comment period. 

SUMMARY: We are revising an earlier 

proposed airworthiness directive (AD) 

for certain The Boeing Company Model 

747–100, 747–100B, 747–100B SUD, 

747–200B, 747–200C, 747–200F, 747– 

300, 747–400, 747–400D, 747–400F, 

747SR, and 747SP series airplanes. The 

notice of proposed rulemaking (NPRM) 

proposed to require replacing the wire 

bundles inside the electrical conduit of 

the forward and aft boost pumps of the 

numbers 1 and 4 main fuel tanks with 

new, improved wire bundles inserted 

into conduit liners. The NPRM was 

prompted by several reports of chafing 

of the wire bundles inside the electrical 

conduit of the forward and aft boost 

pumps of the numbers 1 and 4 main fuel 

tanks due to high vibration. These wire 

bundles can chafe through the wire 

sleeving into the insulation, exposing 

the wire conductors. This action revises 

the NPRM by adding a revision to the 

maintenance or inspection program, as 

applicable, to include critical design 

configuration control limitations 

(CDCCL) for the fuel boost pump wiring. 

We are proposing this SNPRM to 

prevent chafing of the wire bundles and 

subsequent arcing between the wiring 

and the electrical conduit creating an 

ignition source in the fuel tanks, which 

could result in a fire and consequent 

fuel tank explosion. 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 SNPRM by April 22, 2016. 

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 SNPRM, 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 view 

this 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. Boeing Alert Service 

Bulletin 747–28A2306, dated October 2, 

2014, is also available on the Internet at 

http://www.regulations.gov by searching 

for and locating Docket No. FAA–2015– 

0935. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 


asabaliauskas on DSK3SPTVN1PROD with PROPOSALS
12042 Federal Register / Vol. 81, No. 45 / Tuesday, March 8, 2016 / Proposed Rules 

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

0935; 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: 

Tung Tran, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6505; fax: 

425–917–6590; email: tung.tran@

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–2015–0935; Directorate Identifier 

2014–NM–243–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 by adding an AD that would 

apply to certain The Boeing Company 

Model 747–100, 747–100B, 747–100B 

SUD, 747–200B, 747–200C, 747–200F, 

747–300, 747–400, 747–400D, 747– 

400F, 747SR, and 747SP series 

airplanes. The NPRM published in the 

Federal Register on May 1, 2015 (80 FR 

24850) (‘‘the NPRM’’). The NPRM 

proposed to require replacing the wire 

bundles inside the electrical conduit of 

the forward and aft boost pumps of the 

numbers 1 and 4 main fuel tanks with 

new, improved wire bundles inserted 

into conduit liners. 

Actions Since the NPRM was Issued 

Since we issued the NPRM, we have 

determined that it is necessary to revise 

the NPRM by adding a revision to the 

maintenance or inspection program, as 

applicable, to include critical design 

configuration control limitations 

(CDCCL) for the fuel boost pump wiring. 

Related AD 

AD 2011–15–03, Amendment 39– 

16750 (76 FR 41659, July 15, 2011) (‘‘AD 

2011–15–03’’), superseded AD 97–26– 

07, Amendment 39–10250 (62 FR 

65352, December 12, 1997), and requires 

repetitive inspections to detect damage 

of the sleeving and wire bundles of the 

boost pumps of the numbers 1 and 4 

main fuel tanks, and of the auxiliary 

tank jettison pumps (if installed); 

replacement of any damaged sleeving 

with new sleeving; and repair or 

replacement of any damaged wires with 

new wires. For airplanes on which any 

burned wires are found, AD 2011–15–03 

also requires an inspection to detect 

damage of the conduit, and replacement 

of any damaged conduit with a 

serviceable conduit. AD 2011–15–03 

reduced the initial compliance time and 

repetitive inspection interval in AD 97– 

26–07. AD 2011–15–03 was prompted 

by fleet information indicating that the 

repetitive inspection interval in AD 97– 

26–07 was too long because excessive 

chafing of the sleeving continued to 

occur much earlier than expected 

between scheduled inspections. 

Accomplishing the replacement 

specified in this proposed AD would 

terminate the inspections required by 

paragraphs (g), (h), and (n) of AD 2011– 

15–03. 

Comments 

We gave the public the opportunity to 

comment on the NPRM. The following 

presents the comments received on the 

NPRM and the FAA’s response to each 

comment. 

Support for the NPRM 

Boeing concurred with the contents of 

the NPRM. 

Request To Withdraw the NPRM 

UPS recommended that we withdraw 

the NPRM so that UPS can continue 

doing the inspections required by AD 

2011–15–03. UPS stated that it has been 

inspecting the forward and aft boost 

pump wire bundles and sleeving since 

2007 per the requirements in AD 2011– 

15–03, and is satisfied with the current 

inspection, which detects signs of wear 

before major damage occurs. UPS added 

that the wire bundle replacement in this 

NPRM is a burden to the airlines, 

without adding safety to the boost pump 

or airplane fuel system. 

We do not agree with the commenter’s 

request to withdraw the NPRM. We 

agree that the inspection required by AD 

2011–15–03 is likely to detect signs of 

wear before major damage occurs, but 

the potential for an ignition source 

inside the fuel tank due to the single 

failure condition still exists. The 

manufacturer has now developed an 

improved wire bundle installation that 

eliminates the single failure condition. 

We have determined that installation of 

the improved design is required to 

eliminate the need for periodic 

maintenance and inspections in order to 

ensure safety. 

Request To Change Paragraph (g) of the 

Proposed AD (in the NPRM) 

United Airlines (United) asked that 

paragraph (g) of the proposed AD (in the 

NPRM) be changed to add paragraphs 

(g), (h), (i), (j), and (k) of AD 2011–15– 

03, to the language which terminates the 

repetitive inspections required by 

paragraph (n) of AD 2011–15–03. United 

stated that those paragraphs are also 

terminated after doing the wire bundle 

replacement required by paragraph (g) 

of the proposed AD (in the NPRM). 

We agree to add paragraphs (g) and (h) 

of AD 2011–15–03, to the terminating 

action language specified in paragraph 

(g) of this proposed AD, because the 

replacement required by this proposed 

AD would terminate the inspections 

required by paragraphs (g) and (h) of AD 

2011–15–03. However, paragraphs (i), 

(j), and (k) of AD 2011–15–03 are oncondition corrective actions, which 

must be done depending on the findings 

during any inspection required by 

paragraph (g) or (h) of AD 2011–15–03. 

Therefore, we have not referenced 

paragraphs (i), (j), and (k) of AD 2011– 

15–03 in paragraph (g) of this proposed 

AD. 

Request To Add AWL Items 

United stated that incorporating 

airworthiness limitation (AWL) tasks 

28–AWL–24 (747 CL Certification 

Maintenance Requirements) and 28– 

AWL–35 (747–400 Maintenance 

Planning Data) should also be required 

by the NPRM. 

We agree that this proposed AD 

should include revising the 

maintenance or inspection program, as 

applicable, by incorporating the CDCCL 

tasks related to accomplishing Boeing 

Alert Service Bulletin 747–28A2306, 

dated October 2, 2014; therefore, we 

have added new paragraphs (h) and (i) 

to this proposed AD to include those 

requirements. We have redesignated 

subsequent paragraphs accordingly. 


asabaliauskas on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 81, No. 45 / Tuesday, March 8, 2016 / Proposed Rules 12043 

Related Service Information Under 1 

CFR Part 51 

We reviewed the following service 

information: 

• Boeing Alert Service Bulletin 747– 

28A2306, dated October 2, 2014. The 

service information describes 

procedures for replacing the wire 

bundles of the electrical conduit inside 

the electrical conduit of the forward and 

aft boost pumps of the numbers 1 and 

4 main fuel tanks. 

• AWL No. 28–AWL–24, ‘‘Fuel Boost 

Pump Wires In Conduit Installation—In 

Fuel Tank,’’ of Sub-section C.1, ‘‘Fuel 

Tank Ignition Prevention,’’ of Section 

C., ‘‘Airworthiness Limitations— 

Systems,’’ of the Boeing 747–100/200/

300/SP Airworthiness Limitations 

(AWLs) and Certification Maintenance 

Requirements (CMRs) Document D6– 

13747–CMR, Revision June 2014. The 

service information describes a CDCCL 

for the fuel boost pump wiring. 

• AWL No. 28–AWL–35, ‘‘Fuel Boost 

Pump Wires In Conduit Installation—In 

Fuel Tank,’’ of Sub-section B.1, ‘‘Fuel 

System Ignition Prevention,’’ of Section 

B, ‘‘Airworthiness Limitations (AWLs)— 

Systems,’’ of Section 9, Airworthiness 

Limitations (AWLs) and Certification 

Maintenance Requirements (CMRs), of 

Boeing 747–400 Maintenance Planning 

Data (MPD) Document D621U400–9, 

Revision June 2014. The service 

information describes a CDCCL for the 

fuel boost pump wiring. 

This service information is reasonably 

available because the interested parties 

have access to it through their normal 

course of business or by the means 

identified in the ADDRESSES section. 

FAA’s Determination 

We are proposing this SNPRM 

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 

NPRM (80 FR 24850, May 1, 2013). 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 SNPRM. 

Proposed Requirements of This SNPRM 

This SNPRM would require 

accomplishing the actions specified in 

Boeing Alert Service Bulletin 747– 

28A2306, dated October 2, 2014, 

described previously. This SNPRM 

would also require revising the 

maintenance or inspection program, as 

applicable, to include CDCCLs for the 

fuel boost pump wiring. 

This AD requires revisions to certain 

operator maintenance documents to 

include new actions (e.g., inspections) 

and CDCCLs. Compliance with these 

actions and 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 

proposed 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 (j) of this AD. 

The request should include a 

description of changes to the required 

actions that will ensure the continued 

damage tolerance of the affected 

structure. 

Notwithstanding any other 

maintenance or operational 

requirements, components that have 

been identified as airworthy or installed 

on the affected airplanes before 

accomplishing the revision of the 

airplane maintenance or inspection 

program specified in this proposed AD 

do not need to be reworked in 

accordance with the CDCCLs. However, 

once the airplane maintenance or 

inspection program has been revised as 

required by this proposed AD, future 

maintenance actions on these 

components must be done in 

accordance with the CDCCLs. 

Costs of Compliance 

We estimate that this proposed AD 

affects 176 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 Cost on U.S. operators 

Replacement ..................... Up to 53 work-hours × $85 per hour = 

$4,505.

$4,600 Up to $9,105 ..................... Up to $1,602,480. 

Revise maintenance or inspection program.1 work-hour × $85 per hour = $85 ........ 0 $85 .................................... $14,960. 

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 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, 


asabaliauskas on DSK3SPTVN1PROD with PROPOSALS
12044 Federal Register / Vol. 81, No. 45 / Tuesday, March 8, 2016 / Proposed Rules 

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– 

2015–0935; Directorate Identifier 2014– 

NM–243–AD. 

(a) Comments Due Date 

We must receive comments by April 22, 

2016. 

(b) Affected ADs 

This AD affects AD 2011–15–03, 

Amendment 39–16750 (76 FR 41659, July 15, 

2011). 

(c) Applicability 

This AD applies to The Boeing Company 

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

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

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

747SP series airplanes, certificated in any 

category, as identified in Boeing Alert 

Service Bulletin 747–28A2306, dated October 

2, 2014. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 28, Fuel. 

(e) Unsafe Condition 

This AD was prompted by several reports 

of chafing of the wire bundles inside the 

electrical conduit of the forward and aft boost 

pumps of the numbers 1 and 4 main fuel 

tanks due to high vibration. These wire 

bundles can chafe through the wire sleeving 

into the insulation, exposing the wire 

conductors. We are issuing this AD to 

prevent chafing of the wire bundles and 

subsequent arcing between the wiring and 

the electrical conduit creating an ignition 

source in the fuel tanks, which could result 

in a fire and consequent fuel tank explosion. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Replacement 

Within 60 months after the effective date 

of this AD: Replace the wire bundles inside 

the electrical conduit of the forward and aft 

boost pumps of the numbers 1 and 4 main 

fuel tanks with new, improved wire bundles 

inserted into conduit liners, in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–28A2306, 

dated October 2, 2014. Accomplishing the 

replacement required by this paragraph 

terminates the inspections required by 

paragraphs (g), (h), and (n) of AD 2011–15– 

03, Amendment 39–16750 (76 FR 41659, July 

15, 2011). 

(h) Maintenance or Inspection Program 

Revision 

Within 180 days after the effective date of 

this AD, revise the maintenance or inspection 

program, as applicable, to incorporate critical 

design configuration control limitation 

(CDCCL) Task AWL No. 28–AWL–24, ‘‘Fuel 

Boost Pump Wires In Conduit Installation— 

In Fuel Tank,’’ of Sub-section C.1, ‘‘Fuel 

Tank Ignition Prevention,’’ of Section C., 

‘‘Airworthiness Limitations—Systems,’’ of 

the Boeing 747–100/200/300/SP 

Airworthiness Limitations (AWLs) and 

Certification Maintenance Requirements 

(CMRs) Document D6–13747–CMR, Revision 

June 2014; or CDCCL Task No. AWL No. 28– 

AWL–35, ‘‘Fuel Boost Pump Wires In 

Conduit Installation—In Fuel Tank,’’ of Subsection B.1, ‘‘Fuel System Ignition 

Prevention,’’ of Section B, ‘‘Airworthiness 

Limitations (AWLs)—Systems,’’ of Section 9, 

Airworthiness Limitations (AWLs) and 

Certification Maintenance Requirements 

(CMRs), of Boeing 747–400 Maintenance 

Planning Data (MPD) Document D621U400– 

9, Revision June 2014; as applicable. 

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

CDCCLs 

After accomplishing the revision required 

by paragraph (h) 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 (j) of this AD. 

(j) 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 

paragraph (k)(1) of this AD. Information may 

be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@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, 

modification, or alteration 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. To be 

approved, the repair method, modification 

deviation, or alteration deviation must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(k) Related Information 

(1) For more information about this AD, 

contact Tung Tran, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, Seattle 

ACO, 1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6505; fax: 425– 

917–6590; email: tung.tran@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; phone: 206–544– 

5000, extension 1; fax: 206–766–5680; 

Internet: https://www.myboeingfleet.com. 

You may view this 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 February 

18, 2016. 

Dorr M. Anderson, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–04681 Filed 3–7–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–4220; Directorate 

Identifier 2015–NM–076–AD] 

RIN 2120–AA64 

Airworthiness Directives; BAE 

Systems (Operations) Limited 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

Airworthiness Directive (AD) 2011–24– 

06, for all BAE Systems (Operations) 

Limited Model Avro 146–RJ series 

airplanes. AD 2011–24–06 currently 

requires revising the maintenance 

program to incorporate life limits for 

certain items, adding new and more 

restrictive inspections to detect fatigue 

cracking in certain structures, and 

adding fuel system critical design 

configuration control limitations 

(CDCCLs) to prevent ignition sources in 

the fuel tanks. AD 2011–24–06 also 

currently requires modifying the main 

fittings of the main landing gear (MLG) 

and revising the maintenance program 

to incorporate new life limits on MLG 

up-locks and door up-locks and other 

MLG components. Since we issued AD 

2011–24–06, we have determined that 

new or revised structural inspection 

requirements are necessary. This 

proposed AD would require revising the 

maintenance or inspection program, as 

applicable, to incorporate new or 

revised structural inspection 

requirements. We are proposing this AD 

to detect and correct fatigue cracking of 


asabaliauskas on DSK3SPTVN1PROD with PROPOSALS