9370 Federal Register / Vol. 81, No. 37 / Thursday, February 25, 2016 / Proposed Rules 

Service Bulletin 767–53A0260, dated August 

26, 2014. Do all applicable corrective actions 

before further flight. Repeat the inspections 

thereafter at the applicable times specified in 

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

Alert Service Bulletin 767–53A0260, dated 

August 26, 2014. If any existing external 

repair is found in the inspection area, then 

the inspections in Part 1 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 767–53A0260, dated August 

26, 2014, are not required in the area hidden 

by the repair, provided that the repair was 

previously approved by the Manager, Seattle 

Aircraft Certification Office (ACO), or by the 

Authorized Representative of the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA), or 

installed as specified in Part 2 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 767–53A0260, dated August 

26, 2014. Inspections in Part 1 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 767–53A0260, dated August 

26, 2014, remain applicable in areas not 

hidden by the repair. 

(h) Exception to the Service Information 

Where Boeing Alert Service Bulletin 767– 

53A0260, dated August 26, 2014, specifies a 

compliance time ‘‘after the original issue date 

of this service bulletin,’’ this AD requires 

compliance within the specified compliance 

time after the effective date of this AD. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle 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 (i) 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 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) Except as required by paragraph (h) of 

this AD: 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) 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 Wayne Lockett, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

ACO, 1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6447; fax: 425– 

917–6590; email: wayne.lockett@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 

15, 2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–03698 Filed 2–24–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–3702; Directorate 

Identifier 2015–NM–103–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 

Airworthiness Directive (AD) 2013–24– 

12, which applies to all The Boeing 

Company Model 747–8 and 747–8F 

airplanes. AD 2013–24–12 currently 

requires repetitive ultrasonic or dye 

penetrant inspections for cracking of the 

barrel nuts and bolts on each forward 

engine mount, and related investigative 

and corrective actions if necessary. 

Since we issued AD 2013–24–12, we 

have determined that it is necessary to 

mandate the installation of new barrel 

nuts or new inspections to adequately 

address the unsafe condition. This 

proposed AD would retain the 

requirements of AD 2013–24–12 and 

add requirements to install new barrel 

nuts at the forward engine mounts; or 

identify the part number of the barrel 

nuts, inspect affected barrel nuts for 

gaps of the strut bulkhead and forward 

engine mount, and do related 

investigative and corrective actions if 

necessary. This proposed AD would 

also remove airplanes from the 

applicability. We are proposing this AD 

to detect and correct cracked barrel nuts 

on a forward engine mount, which 

could result in reduced load capacity of 

the forward engine mount, separation of 

an engine under power from the 

airplane, and consequent loss of control 

of the airplane. 

DATES: We must receive comments on 

this proposed AD by April 11, 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: 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 NPRM, 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. It is also available 

on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2016– 

3702. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2016– 

3702; 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 


rmajette on DSK2TPTVN1PROD with PROPOSALS
Federal Register / Vol. 81, No. 37 / Thursday, February 25, 2016 / Proposed Rules 9371 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Nathan Weigand, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office 

(ACO), 1601 Lind Avenue SW., Renton, 

WA 98057–3356; phone: 425–917–6428; 

fax: 425–917–6590; email: 

Nathan.p.weigand@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–2016–3702; Directorate Identifier 

2015–NM–103–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 November 19, 2013, we issued AD 

2013–24–12, Amendment 39–17686 (78 

FR 71989, December 2, 2013) (‘‘AD 

2013–24–12’’), for all The Boeing 

Company Model 747–8 and 747–8F 

airplanes. AD 2013–24–12 requires 

repetitive ultrasonic or dye penetrant 

inspections for cracking of the barrel 

nuts and bolts, as applicable, on each 

forward engine mount, and related 

investigative and corrective actions if 

necessary. AD 2013–24–12 resulted 

from a report of cracked barrel nuts 

found on a forward engine mount. We 

issued AD 2013–24–12 to detect and 

correct cracked barrel nuts on a forward 

engine mount, which could result in 

reduced load capacity of the forward 

engine mount, separation of an engine 

under power from the airplane, and 

consequent loss of control of the 

airplane. 

Actions Since AD 2013–24–12 Was 

Issued 

The preamble to AD 2013–24–12 

explains that we considered 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. 

Related Service Information Under 1 

CFR Part 51 

We reviewed the following service 

information: 

• Boeing Service Bulletin 747– 

71A2329, Revision 1, dated May 28, 

2015. The service information describes 

procedures for inspecting for cracked 

bolts and barrel nuts on the forward 

engine mounts, replacing cracked bolts 

and barrel nuts, and sending the 

inspection results and cracked parts to 

Boeing. 

• Boeing Special Attention Service 

Bulletin 747–71–2332, Revision 1, dated 

May 28, 2015. The service information 

describes procedures for installing new 

barrel nuts, inspecting the barrel nuts at 

the forward engine mount to determine 

the part number (P/N), inspecting for 

gaps of the strut bulkhead and forward 

engine mount, and doing applicable 

related investigative and corrective 

actions. 

• 747–8/–8F Airworthiness 

Limitation (AWL), Document Number 

D011U721–02–01, dated September 

2015, which includes a limitation for 

Structurally Significant Item (SSI) 54– 

50–003c, which describes procedures 

for structural inspections. 

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 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 all 

requirements of AD 2013–24–12. This 

proposed AD would also require 

accomplishing the actions specified in 

Boeing Special Attention Service 

Bulletin 747–71–2332, Revision 1, dated 

May 28, 2015, described previously, 

except as discussed under ‘‘Differences 

Between Proposed AD and Service 

Information.’’ For information on the 

procedures and compliance times, see 

this service information at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2016– 

3702. 

The phrase ‘‘related investigative 

actions’’ is used in this proposed AD. 

‘‘Related investigative actions’’ are 

follow-on actions that (1) are related to 

the primary action, and (2) further 

investigate the nature of any condition 

found. Related investigative actions in 

an AD could include, for example, 

inspections. 

The phrase ‘‘corrective actions’’ is 

used in this proposed AD. ‘‘Corrective 

actions’’ are actions that correct or 

address any condition found. Corrective 

actions in an AD could include, for 

example, repairs. 

Differences Between Proposed AD and 

Service Information 

Boeing Special Attention Service 

Bulletin 747–71–2332, Revision 1, dated 

May 28, 2015, specifies to contact the 

manufacturer for instructions on how to 

repair certain conditions, but this 

proposed AD would require repairing 

those conditions in one of the following 

ways: 

• In accordance with a method that 

we approve; or 

• Using data that meet the 

certification basis of the airplane, and 

that have been approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) whom 

we have authorized to make those 

findings. 

Costs of Compliance 

We estimate that this proposed AD 

affects 7 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 

Inspections (retained actions from AD 2013– 

24–12).

Up to 24 work-hours × $85 per 

hour = $2,040 per inspection 

cycle.

$0 Up to $2,040 per inspection cycle.Up to $14,280 per inspection cycle. 

Installation (new proposed action) ................. 17 work-hours × $85 per hour = 

$1,445.

6,384 $7,829 ....................... Up to $54,803. 


rmajette on DSK2TPTVN1PROD with PROPOSALS
9372 Federal Register / Vol. 81, No. 37 / Thursday, February 25, 2016 / Proposed Rules 

ESTIMATED COSTS—Continued 

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

operators 

Inspections (new proposed alternative actions).4 work-hours × $85 per hour = 

$340.

0 $340 .......................... Up to $2,380. 

Maintenance program revision (new proposed requirement).1 work-hour × $85 per hour = 

$85.

0 $85 ............................ $595. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the bootstrap installation 

specified in this proposed AD. We 

estimate the following costs to do other 

necessary related investigative and 

corrective actions that would be 

required based on the results of the 

proposed inspection. We have no way of 

determining the number of aircraft that 

might need these actions: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Ultrasonic inspection ......................................................... 5 work-hours × $85 per hour = $425 ............................... $0 $425 

According to the manufacturer, some 

of the costs of this proposed AD may be 

covered under warranty, thereby 

reducing the cost impact on affected 

individuals. We do not control warranty 

coverage for affected individuals. As a 

result, we have included all costs in our 

cost estimate. 

Paperwork Reduction Act 

A federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject 

to penalty for failure to comply with a 

collection of information subject to the 

requirements of the Paperwork 

Reduction Act unless that collection of 

information displays a current valid 

Office of Management and Budget 

(OMB) control number. The control 

number for the collection of information 

required by this AD is 2120–0056. The 

paperwork cost associated with this AD 

has been detailed in the Costs of 

Compliance section of this document 

and includes time for reviewing 

instructions, as well as completing and 

reviewing the collection of information. 

Therefore, all reporting associated with 

this AD is mandatory. Comments 

concerning the accuracy of this burden 

and suggestions for reducing the burden 

should be directed to the FAA at 800 

Independence Ave. SW., Washington, 

DC 20591. ATTN: Information 

Collection Clearance Officer, AES–200. 

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) 

2013–24–12, Amendment 39–17686 (78 

FR 71989, December 2, 2013), and 

adding the following new AD: 

The Boeing Company: Docket No. FAA– 

2016–3702; Directorate Identifier 2015– 

NM–103–AD. 

(a) Comments Due Date 

The FAA must receive comments on this 

AD action by April 11, 2016. 

(b) Affected ADs 

This AD replaces AD 2013–24–12, 

Amendment 39–17686 (78 FR 71989, 

December 2, 2013). 

(c) Applicability 

This AD applies to The Boeing Company 

Model 747–8F and 747–8 airplanes, 

certificated in any category, as identified in 

Boeing Service Bulletin 747–71A2329, 

Revision 1, dated May 28, 2015. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 71, Powerplant. 


rmajette on DSK2TPTVN1PROD with PROPOSALS
Federal Register / Vol. 81, No. 37 / Thursday, February 25, 2016 / Proposed Rules 9373 

(e) Unsafe Condition 

This AD was prompted by a report of 

cracked barrel nuts found on a forward 

engine mount, and by the determination that 

additional actions are necessary to address 

the unsafe condition. We are issuing this AD 

to detect and correct cracked barrel nuts on 

a forward engine mount, which could result 

in reduced load capacity of the forward 

engine mount, separation of an engine under 

power from the airplane, and consequent loss 

of control of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Repetitive Inspections and 

Corrective Actions, With Revised Service 

Information 

This paragraph restates the actions 

required by paragraph (g) of AD 2013–24–12, 

Amendment 39–17686 (78 FR 71989, 

December 2, 2013) (‘‘AD 2013–24–12’’), with 

revised service information: Except as 

required by paragraph (h)(1) of this AD, at the 

time specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–71A2329, dated September 27, 

2013: Do the inspection specified in 

paragraph (g)(1) or (g)(2) of this AD, and do 

all applicable related investigative and 

corrective actions, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–71A2329, dated 

September 27, 2013; or Boeing Service 

Bulletin 747–71A2329, Revision 1, dated 

May 28, 2015. Do all applicable related 

investigative and corrective actions before 

further flight. Repeat the inspection 

thereafter at the times specified in paragraph 

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

Bulletin 747–71A2329, dated September 27, 

2013. As of the effective date of this AD, use 

only Boeing Service Bulletin 747–71A2329, 

Revision 1, dated May 28, 2015. 

(1) Ultrasonic inspection for cracking of the 

barrel nuts on each forward engine mount, 

except as required by paragraph (h)(2) of this 

AD. 

(2) Dye penetrant inspection for cracking of 

the bolts and barrel nuts. Whenever a dye 

penetrant inspection is done, all the bolts 

and barrel nuts on that engine mount must 

be removed and replaced with new or 

serviceable parts. 

(h) Retained Exceptions to Service 

Information Specifications, With Revised 

Service Information References 

(1) Where Boeing Alert Service Bulletin 

747–71A2329, dated September 27, 2013; or 

Boeing Service Bulletin 747–71A2329, 

Revision 1, dated May 28, 2015; specify a 

compliance time ‘‘after the original issue date 

of this service bulletin,’’ this AD requires 

compliance within the specified compliance 

time after December 17, 2013 (the effective 

date of AD 2013–24–12). 

(2) Where Appendix B of Boeing Alert 

Service Bulletin 747–71A2329, dated 

September 27, 2013, and Appendix B of 

Boeing Service Bulletin 747–71A2329, 

Revision 1, dated May 28, 2015, state that 

alternate instruments and transducers can be 

used, this AD requires that only equivalent 

instruments and transducers can be used. 

(3) Where Appendix A of Boeing Alert 

Service Bulletin 747–71A2329, dated 

September 27, 2013, and Appendix A of 

Boeing Service Bulletin 747–71A2329, 

Revision 1, dated May 28, 2015, state to 

record flight hours and flight cycles, record 

the flight hours and flight cycles on the 

airplane and the flight hours and flight cycles 

for each engine since change or removal. 

(i) Retained Reporting and Sending Parts, 

With Revised Service Information 

After any inspection required by paragraph 

(g) of this AD: Submit a report of the 

inspection results (both positive and 

negative), and return all cracked bolts and 

barrel nuts, at the applicable time specified 

in paragraph (i)(1) or (i)(2) of this AD. The 

report must include the information 

requested in Appendix A of Boeing Alert 

Service Bulletin 747–71A2329, dated 

September 27, 2013, or Appendix A of 

Boeing Service Bulletin 747–71A2329, 

Revision 1, dated May 28, 2015, except as 

required by paragraph (h)(3) of this AD. Both 

the report and all cracked bolts and barrel 

nuts must be sent to the address specified in 

Appendix A of Boeing Alert Service Bulletin 

747–71A2329, dated September 27, 2013, or 

Appendix A of Boeing Service Bulletin 747– 

71A2329, Revision 1, dated May 28, 2015. 

(1) For airplanes on which an ultrasonic 

inspection was done and no cracking was 

found, do the required actions at the time 

specified in paragraph (i)(1)(i) or (i)(1)(ii) of 

this AD, as applicable. 

(i) If the inspection was done on or after 

December 17, 2013 (the effective date of AD 

2013–24–12): Submit the report within 10 

days after the inspection. 

(ii) If the inspection was done before 

December 17, 2013 (the effective date of AD 

2013–24–12): Submit the report within 10 

days after December 17, 2013 (the effective 

date of AD 2013–24–12). 

(2) For airplanes on which a dye penetrant 

inspection was done, do the required actions 

at the time specified in paragraph (i)(2)(i) or 

(i)(2)(ii) of this AD, as applicable. 

(i) If the inspection was done on or after 

December 17, 2013 (the effective date of AD 

2013–24–12): Submit the report and return 

all cracked bolts and barrel nuts within 10 

days after replacing the bolts and barrel nuts 

with new or serviceable bolts and barrel nuts 

in accordance with Part 2 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–71A2329, dated 

September 27, 2013; or Boeing Service 

Bulletin 747–71A2329, Revision 1, dated 

May 28, 2015. 

(ii) If the inspection was done before 

December 17, 2013 (the effective date of AD 

2013–24–12): Submit the report and return 

all cracked bolts and barrel nuts within 10 

days after December 17, 2013 (the effective 

date of AD 2013–24–12). 

(j) Retained Paperwork Reduction Act 

Burden Statement, With No Changes 

A federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject to 

a penalty for failure to comply with a 

collection of information subject to the 

requirements of the Paperwork Reduction 

Act unless that collection of information 

displays a current valid Office of 

Management and Budget (OMB) Control 

Number. The OMB Control Number for this 

information collection is 2120–0056. Public 

reporting for this collection of information is 

estimated to be approximately 5 minutes per 

response, including the time for reviewing 

instructions, completing and reviewing the 

collection of information. All responses to 

this collection of information are mandatory. 

Comments concerning the accuracy of this 

burden and suggestions for reducing the 

burden should be directed to the FAA at: 800 

Independence Ave. SW., Washington, DC 

20591, Attn: Information Collection 

Clearance Officer, AES–200. 

(k) New Installation or Inspections 

At the applicable time specified in 

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

Special Attention Service Bulletin 747–71– 

2332, Revision 1, dated May 28, 2015, except 

as required by paragraph (o)(1) of this AD: Do 

the actions specified in paragraph (k)(1) or 

(k)(2) of this AD, in accordance with the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 747–71– 

2332, Revision 1, dated May 28, 2015, except 

as required by paragraph (o)(2) of this AD. 

(1) Install new barrel nuts using the 

bootstrap installation method identified in 

Part 1 of the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

747–71–2332, Revision 1, dated May 28, 

2015. 

(2) Do a general visual inspection to 

determine the part number (P/N) of the barrel 

nuts at the forward engine mount. If any 

barrel nut P/N SL4081C14SP1 is installed, 

before further flight, do a general visual 

inspection for gaps of the strut bulkhead and 

forward engine mount to determine if the 

nut-by-but method identified in Part 4 of the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 747–71– 

2332, Revision 1, dated May 28, 2015, can be 

used, and do all applicable related 

investigative and corrective actions. Do all 

applicable related investigative and 

corrective actions before further flight, 

including the nut-by-nut replacement 

identified in Part 4 of the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 747–71–2332, Revision 1, 

dated May 28, 2015. If the nut-by-nut 

replacement identified in Part 4 of the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 747–71– 

2332, Revision 1, dated May 28, 2015 cannot 

be accomplished, install new nuts, in 

accordance with paragraph (k)(1) of this AD. 

(l) Maintenance Program Revision 

Within 30 days after accomplishment of 

the actions required by paragraph (k) of this 

AD, or within 30 days after the effective date 

of this AD, whichever occurs later: Revise the 

maintenance or inspection program, as 

applicable, to incorporate the 747–8/–8F 

Airworthiness Limitation (AWL), Document 

Number D011U721–02–01, Structurally 

Significant Item (SSI) 54–50–003c. 


rmajette on DSK2TPTVN1PROD with PROPOSALS
9374 Federal Register / Vol. 81, No. 37 / Thursday, February 25, 2016 / Proposed Rules 

(m) Terminating Action 

Accomplishment of the actions required by 

paragraphs (k) and (l) of this AD terminate 

the requirements of paragraphs (g) and (i) of 

this AD. 

(n) Parts Installation Prohibition 

As of the effective date of this AD, no 

person may install or reinstall any barrel nut 

P/N SL4081C14SP1 at the forward engine 

mount assembly on any airplane, and only P/ 

N SL4750NA may be installed. 

(o) New Exceptions to Service Information 

Specifications 

(1) Where Boeing Special Attention Service 

Bulletin 747–71–2332, Revision 1, dated May 

28, 2015, specifies a compliance time ‘‘after 

the original issue date of this service 

bulletin,’’ this AD requires compliance 

within the specified compliance time after 

the effective date of this AD. 

(2) Where Boeing Special Attention Service 

Bulletin 747–71–2332, Revision 1, dated May 

28, 2015, specifies to contact Boeing for 

appropriate action: Before further flight, 

repair using a method approved in 

accordance with the procedures specified in 

paragraph (r) of this AD. 

(p) No Alternative Actions or Intervals 

After the maintenance or inspection 

program has been revised as required by 

paragraph (l) 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 (r) of this 

AD. 

(q) Credit for Previous Actions 

This paragraph provides credit for the 

actions specified in paragraph (k) of this AD, 

if those actions were performed before the 

effective date of this AD using Boeing Special 

Attention Service Bulletin 747–71–2332, 

dated May 30, 2014, which is not 

incorporated by reference in this AD. 

(r) 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 (s)(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) AMOCs approved for AD 2013–24–12 

are approved as AMOCs for the 

corresponding provisions of this AD. 

(5) Except as required by paragraph (o)(2) 

of this AD: For service information that 

contains steps that are labeled as Required 

for Compliance (RC), the provisions of 

paragraphs (r)(5)(i) and (r)(5)(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. 

(s) Related Information 

(1) For more information about this AD, 

contact Nathan Weigand, Aerospace 

Engineer, Airframe Branch, ANM–120S, 

FAA, Seattle ACO, 1601 Lind Avenue SW., 

Renton, WA 98057–3356; phone: 425–917– 

6428; fax: 425–917–6590; email: 

Nathan.p.weigand@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 

15, 2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–03690 Filed 2–24–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–3701; Directorate 

Identifier 2015–NM–015–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

Airworthiness Directive (AD) 2013–25– 

08, for all Airbus Model A330–200, 

–200 Freighter, and –300 series 

airplanes; and Model A340–200 and 

–300 series airplanes. AD 2013–25–08 

currently requires a repetitive 

inspection program on certain check 

valves in the hydraulic systems that 

includes, among other things, 

inspections for lock wire presence and 

integrity, traces of seepage or black 

deposits, proper torque, alignment of 

the check valve and manifold, 

installation of new lock wire, and 

corrective actions if needed. Since we 

issued AD 2013–25–08, Airbus has 

developed an improved check valve. 

This proposed AD would add airplanes 

to the applicability, and require 

modifying the green, blue and yellow 

high pressure hydraulic manifolds by 

replacing certain check valves with 

improved check valves, which would 

terminate the repetitive inspections 

required by this proposed AD. We are 

proposing this AD to detect and correct 

hydraulic check valve loosening; 

loosened valves could result in 

hydraulic leaks, possibly leading to the 

loss of all three hydraulic systems and 

consequent loss of control of the 

airplane. 

DATES: We must receive comments on 

this proposed AD by April 11, 2016. 

ADDRESSES: You may send comments 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, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this NPRM, contact Airbus SAS— 

Airworthiness Office—EAL, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 45 80; email 

airworthiness.A330–A340@airbus.com; 

Internet http://www.airbus.com. You 

may view this referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, WA. For information on 


rmajette on DSK2TPTVN1PROD with PROPOSALS