60248 Federal Register / Vol. 81, No. 170 / Thursday, September 1, 2016 / Rules and Regulations 

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on August 

24, 2016. 

John P. Piccola, Jr., 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–20991 Filed 8–31–16; 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; Amendment 

39–18634; AD 2016–18–04] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2013–24– 

12 for all The Boeing Company Model 

747–8 and 747–8F airplanes. AD 2013– 

24–12 required 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. This new AD retains the 

requirements of AD 2013–24–12 and 

also requires installing new barrel nuts 

at the forward engine mounts; or 

identifying the part number of the barrel 

nuts, inspecting affected barrel nuts for 

gaps of the strut bulkhead and forward 

engine mount, and doing related 

investigative and corrective actions if 

necessary. This new AD also removes 

airplanes from the applicability. This 

new AD also requires revising the 

maintenance or inspection program, as 

applicable, to include a new structurally 

significant item. This AD was prompted 

by our determination that it is necessary 

to mandate the installation of new barrel 

nuts or new inspections to adequately 

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. 

DATES: This AD is effective October 6, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of October 6, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of December 17, 2013 (78 FR 

71989, December 2, 2013). 

ADDRESSES: For service information 

identified in this final rule, 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 AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Docket Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

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: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2013–24–12, 

Amendment 39–17686 (78 FR 71989, 

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

AD 2013–24–12 applied to all The 

Boeing Company Model 747–8 and 747– 

8F airplanes. The NPRM published in 

the Federal Register on February 25, 

2016 (81 FR 9370) (‘‘the NPRM’’). The 

NPRM was prompted by our 

determination that it is necessary to 

mandate the installation of new barrel 

nuts or new inspections to adequately 

address the unsafe condition. The 

NPRM proposed to retain the 

requirements of AD 2013–24–12 and 

also require installing new barrel nuts at 

the forward engine mounts; or 

identifying the part number of the barrel 

nuts, inspecting affected barrel nuts for 

gaps of the strut bulkhead and forward 

engine mount, and doing related 

investigative and corrective actions if 

necessary. The NPRM also proposed to 

remove airplanes from the applicability. 

The NPRM also proposed to require 

revising the maintenance or inspection 

program, as applicable, to include a new 

structurally significant item. 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. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM and the FAA’s 

response to each comment. 

Support for the NPRM 

Boeing stated that it supports the 

NPRM. 

Request To Revise Applicability 

The Civil Aviation Administration of 

China (CAAC) requested that we revise 

the applicability of the proposed AD to 

ensure that all necessary actions are 

applied on all applicable airplanes. 

CAAC explained that it compared the 

effectivity between Boeing Service 

Bulletin 747–71A2329, Revision 1, 

dated May 28, 2015, which is referred 

to in the applicability of the proposed 

AD, and Boeing Special Attention 

Service Bulletin 747–71–2332, Revision 

1, dated May 28, 2015 (which is referred 

to as the appropriate source of service 

information for doing the actions 

specified in paragraph (k) of the 

proposed AD). CAAC explained that 

there are more airplanes in Boeing 

Special Attention Service Bulletin 747– 

71–2332, Revision 1, dated May 28, 

2015, than in Boeing Service Bulletin 

747–71A2329, Revision 1, dated May 

28, 2015. 

We agree to clarify and revise the 

applicability of this AD. The difference 

in effectivity between Boeing Service 

Bulletin 747–71A2329, Revision 1, 

dated May 28, 2015, and Boeing Special 

Attention Service Bulletin 747–71– 

2332, Revision 1, dated May 28, 2015, 


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is that there are six additional airplanes 

in Boeing Special Attention Service 

Bulletin 747–71–2332, Revision 1, dated 

May 28, 2015—four of these airplanes 

are foreign-registered, and the other two 

airplanes have not been delivered yet. 

We have revised paragraph (c) of this 

AD to refer to Boeing Special Attention 

Service Bulletin 747–71–2332, Revision 

1, dated May 28, 2015. We have also 

revised paragraph (g) of this AD to 

specify that only airplanes identified in 

Boeing Service Bulletin 747–71A2329, 

Revision 1, dated May 28, 2015, are 

affected by that paragraph. 

Request for Explanation of Change in 

Applicability From AD 2013–24–12 

The CAAC requested that we explain 

the change in the applicability 

paragraph of the proposed AD from that 

of AD 2013–24–12. The CAAC 

explained that the applicability 

paragraph of AD 2013–24–12 applies to 

all The Boeing Company Model 747–8 

and 747–8F series airplanes. The CAAC 

stated that the NPRM would retain the 

requirements of AD 2013–24–12, but the 

applicability paragraph of the proposed 

AD only applies to The Boeing 

Company Model 747–8 and 747–8F 

airplanes identified in Boeing Service 

Bulletin 747–71A2329, Revision 1, 

dated May 28, 2015. 

We agree to clarify. AD 2013–24–12 

was issued as an interim action. Boeing 

developed Boeing Special Attention 

Service Bulletin 747–71–2332, dated 

September 27, 2013 (currently at 

Revision 1, dated May 28, 2015), which 

contains a newly designed barrel nut. 

The effectivity in Boeing Service 

Bulletin 747–71A2329, Revision 1, 

dated May 28, 2015, identifies the 

airplanes that did not have the newly 

designed barrel nuts installed upon 

delivery. Because this AD does not 

include airplanes that have the newly 

designed barrel nuts installed during 

production, the applicability of AD 

2013–24–12 was reduced. No changes 

have been made to this AD in this 

regard. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

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, inspecting for gaps of 

the strut bulkhead and forward engine 

mount, and doing applicable related 

investigative and corrective actions. 

• Boeing 747–8/–8F Airworthiness 

Limitations (AWLs), Document Number 

D011U721–02–01, dated September 

2015, which includes a limitation for 

Structurally Significant Item (SSI) 54– 

50–003c. The service information 

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. 

Costs of Compliance 

We estimate that this AD affects 7 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Cost on 

U.S. operators 

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 action) ......................... 17 work-hours × $85 per hour = $1,445 6,384 7,829 ...................... Up to $54,803. 

Inspections (new alternative actions) ..... 4 work-hours × $85 per hour = $340 ..... 0 340 ......................... Up to $2,380. 

Maintenance program revision (new 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 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 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 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 


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60250 Federal Register / Vol. 81, No. 170 / Thursday, September 1, 2016 / Rules and Regulations 

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 

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 AD will 

not have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

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

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing Airworthiness Directive (AD) 

2013–24–12, Amendment 39–17686 (78 

FR 71989, December 2, 2013), and 

adding the following new AD: 

2016–18–04 The Boeing Company: 

Amendment 39–18634; Docket No. 

FAA–2016–3702; Directorate Identifier 

2015–NM–103–AD. 

(a) Effective Date 

This AD is effective October 6, 2016. 

(b) Affected ADs 

This AD replaces AD 2013–24–12, 

Amendment 39–17686 (78 FR 71989, 

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

(c) Applicability 

This AD applies to The Boeing Company 

Model 747–8 and 747–8F airplanes, 

certificated in any category, as identified in 

Boeing Special Attention Service Bulletin 

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

2015. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 71, Powerplant. 

(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, 

with revised service information. For 

airplanes identified in Boeing Service 

Bulletin 747–71A2329, Revision 1, dated 

May 28, 2015: 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 


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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-nut 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 or Inspection 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 Structurally 

Significant Item (SSI) 54–50–003c specified 

in Boeing 747–8/–8F Airworthiness 

Limitations (AWLs), Document Number 

D011U721–02–01, dated September 2015. 

(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 


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60252 Federal Register / Vol. 81, No. 170 / Thursday, September 1, 2016 / Rules and Regulations 

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) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (t)(5) and (t)(6) of this AD. 

(t) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(3) The following service information was 

approved for IBR on October 6, 2016. 

(i) Boeing Service Bulletin 747–71A2329, 

Revision 1, dated May 28, 2015. 

(ii) Boeing Special Attention Service 

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

28, 2015. 

(iii) Boeing 747–8/–8F Airworthiness 

Limitation (AWL), Document Number 

D011U721–02–01, dated September 2015. 

(4) The following service information was 

approved for IBR on December 17, 2013 (78 

FR 71989, December 2, 2013). 

(i) Boeing Alert Service Bulletin 747– 

71A2329, dated September 27, 2013. 

(ii) Reserved. 

(5) 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. 

(6) You may view this 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. 

(7) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http:// 

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on August 

19, 2016. 

Dorr M. Anderson, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–20825 Filed 8–31–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–6414; Directorate 

Identifier 2015–NM–175–AD; Amendment 

39–18633; AD 2016–18–03] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Bombardier, Inc. Model CL–600–2B19 

(Regional Jet Series 100 & 440) 

airplanes. This AD was prompted by 

two in-service incidents of a loss of all 

air data information in the flight deck. 

This AD requires a revision of the 

airplane flight manual (AFM) 

emergency procedures section to 

provide procedures to guide the crew on 

how to stabilize the airplane airspeed 

and attitude for continued safe flight 

when a loss of all air data information 

has occurred in the flight deck. We are 

issuing this AD to prevent loss of 

control when a loss of all air data 

information has occurred in the flight 

deck. 

DATES: This AD is effective October 6, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of October 6, 2016. 

ADDRESSES: For service information 

identified in this final rule, contact 

Bombardier, Inc., 400 Coˆte-Vertu Road 

West, Dorval, Que ́bec H4S 1Y9, Canada; 

telephone 514–855–5000; fax 514–855– 

7401; email thd.crj@

aero.bombardier.com; Internet http://

www.bombardier.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– 

6414. 

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– 

6414; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Office (telephone 800–647– 

5527) is Docket Management Facility, 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue SE., 

Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Assata Dessaline, Aerospace Engineer, 

Avionics and Services Branch, ANE– 

172, FAA, New York Aircraft 

Certification Office (ACO), 1600 Stewart 

Avenue, Suite 410, Westbury, NY 

11590; telephone 516–228–7301; fax 

516–794–5531. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain Bombardier, Inc. Model 

CL–600–2B19 (Regional Jet Series 100 & 

440) airplanes. The NPRM published in 

the Federal Register on May 10, 2016 

(81 FR 28764) (‘‘the NPRM’’). The 

NPRM was prompted by two in-service 

incidents of a loss of all air data 

information in the flight deck. The 

NPRM proposed to require a revision of 

the AFM emergency procedures section 

to provide procedures to guide the crew 

on how to stabilize the airplane airspeed 

and attitude for continued safe flight 

when a loss of all air data information 

has occurred in the flight deck. We are 

issuing this AD to prevent loss of 

control when a loss of all air data 

information has occurred in the flight 

deck. 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2015–12, 

dated June 23, 2015 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for certain Bombardier, Inc. Model CL– 

600–2B19 (Regional Jet Series 100 & 

440) airplanes. The MCAI states: 

Two in-service incidents have been 

reported on CL–600–2C10 aeroplanes 


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