Federal Register / Vol. 81, No. 225 / Tuesday, November 22, 2016 / Rules and Regulations 83657 

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): 

2016–23–04 BRP-Powertrain GmbH & Co 

KG (formerly BRP-Rotax GmbH & Co 

KG, Bombardier-Rotax GmbH & Co. KG, 

and Bombardier-Rotax GmbH): 

Amendment 39–18711; Docket No. 

FAA–2016–9103; Directorate Identifier 

2016–NE–18–AD. 

(a) Effective Date 

This AD is effective December 7, 2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to BRP-Powertrain GmbH 

& Co KG Rotax model 912 F2, 912 F3, 912 

F4, 912 S2, 912 S3, and 912 S4 engines, and 

Rotax 914 F2, 914 F3, and 914 F4 engines 

with: 

(1) Engine serial numbers (S/Ns) listed in 

Planning Information, Paragraph 1, Criterion 

A, of BRP-Powertrain GmbH & Co KG Alert 

Service Bulletin (ASB) ASB–912–069R1/ 

ASB–914–051R1 (one document), Revision 1, 

dated July 22, 2016. 

(2) Carburetor part numbers (P/Ns) and S/ 

Ns listed in Planning Information, Paragraph 

1, Criterion B, of BRP-Powertrain GmbH & Co 

KG ASB ASB–912–069R1/ASB–914–051R1 

(one document), Revision 1, dated July 22, 

2016; or 

(3) Carburetor floats, P/N 861185, that do 

not have 3 dots molded on the surface, and 

installed after May 9, 2016. 

(d) Reason 

This AD was prompted by a report of a 

quality escape in the manufacturing of the 

affected carburetor floats. We are issuing this 

AD to prevent failure of the carburetor float, 

failure of the engine, in-flight shutdown, and 

loss of the airplane. 

(e) Actions and Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) Within 25 flight hours (FHs) or 30 days 

after the effective date of this AD, replace any 

affected carburetor float with a float that is 

eligible for installation in accordance with 

the Accomplishment Instructions, Paragraph 

3, of BRP-Powertrain GmbH & Co KG Rotax 

ASB ASB–912–069R1/ASB–914–051R1 (one 

document), Revision 1, dated July 22, 2016. 

(2) After the effective date of this AD, do 

not install on any engine a carburetor float, 

P/N 861185, delivered between May 8, 2016, 

and July 17, 2016, that does not have 3 dots 

molded into the surface. If the delivery date 

is not documented, do not install the part. 

(f) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

FAA, may approve AMOCs for this AD. Use 

the procedures found in 14 CFR 39.19 to 

make your request. You may email your 

request to: ANE-AD-AMOC@faa.gov. 

(g) Related Information 

(1) For more information about this AD, 

contact Michael Richardson-Bach, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine & Propeller Directorate, 1200 District 

Avenue, Burlington, MA 01803; phone: 781– 

238–7747; fax: 781–238–7199; email: 

michael.richardson-bach@faa.gov. 

(2) Refer to MCAI European Aviation 

Safety Agency AD 2016–0144, dated July 19, 

2016 (corrected July 25, 2016), for more 

information. You may examine the MCAI in 

the AD docket on the Internet at http://

www.regulations.gov by searching for and 

locating it in Docket No. FAA–2016–9103. 

(h) 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. 

(i) BRP-Powertrain GmbH & Co KG Alert 

Service Bulletin ASB–912–069R1/ASB–914– 

051R1 (one document), Revision 1, dated July 

22, 2016. 

(ii) Reserved. 

(3) For BRP-Powertrain GmbH & Co KG 

service information identified in this AD, 

contact BRP-Powertrain GmbH & Co KG, 

Rotaxstrasse 1, A–4623 Gunskirchen, Austria; 

phone: +43 7246 6010; fax: +43 7246 601 

9130; email: airworthiness@brp.com; 

Internet: http://www.FLYROTAX.com. 

(4) You may view this service information 

at FAA, Engine & Propeller Directorate, 1200 

District Avenue, Burlington, MA 01803. For 

information on the availability of this 

material at the FAA, call 781–238–7125. 

(5) You may view this service information 

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 Burlington, Massachusetts, on 

November 7, 2016. 

Ann C. Mollica, 

Acting Directorate Manager, Engine & 

Propeller Directorate, Aircraft Certification 

Service. 

[FR Doc. 2016–27922 Filed 11–21–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–5034; Directorate 

Identifier 2015–NM–172–AD; Amendment 

39–18702; AD 2016–22–13] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all The 

Boeing Company Model 737–600, –700, 

–700C, –800, –900, and –900ER series 

airplanes. This AD was prompted by an 

evaluation by the design approval 

holder (DAH) indicating that lap splices 

for certain stringers are subject to 

widespread fatigue damage (WFD). This 

AD requires repetitive inspections for 

cracking in the lower fastener row of the 

lap splices of certain stringers, and 

repair if necessary. We are issuing this 

AD to address the unsafe condition on 

these products. 

DATES: This AD is effective December 

27, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of December 27, 2016. 

ADDRESSES: For service information 

identified in this final rule, contact 

Boeing Commercial Airplanes, 

Attention: Contractual & Data Services 

(C&DS), 2600 Westminster Blvd., MC 

110–SK57, Seal Beach, CA 90740; 

telephone 562–797–1717; 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– 

5034. 

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– 

5034; 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 


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83658 Federal Register / Vol. 81, No. 225 / Tuesday, November 22, 2016 / Rules and Regulations 

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: 

Gaetano Settineri, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office 

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

WA 98057–3356; phone: 425–917–6577; 

fax: 425–917–6590; email: 

gaetano.settineri@faa.gov. 

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 all The Boeing Company Model 

737–600, –700, –700C, –800, –900, and 

–900ER series airplanes. The NPRM 

published in the Federal Register on 

March 29, 2016 (81 FR 17415) (‘‘the 

NPRM’’). The NPRM was prompted by 

an evaluation by the DAH indicating 

that the S–14L and S–14R lap splices 

are subject to WFD. The NPRM 

proposed to require repetitive low 

frequency eddy current inspections for 

cracking in the lower fastener row of the 

S–14L and S–14R lap splices, and repair 

if necessary. We are issuing this AD to 

detect and correct widespread cracking 

in the S–14L and S–14R lap splices that 

could rapidly link up and result in 

possible rapid decompression and 

reduced structural integrity 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 and a commenter, Jordan 

Ibsen, supported the content of the 

NPRM. 

Effect of Winglets on Accomplishment 

of the Proposed Actions 

Aviation Partners Boeing stated that 

accomplishing the supplemental type 

certificate (STC) ST00830SE does not 

affect compliance with the actions 

specified in the NPRM. 

We agree with the commenter. We 

have redesignated paragraph (c) of the 

NPRM as (c)(1) and added a new 

paragraph (c)(2) to this final rule to state 

that installation of STC ST00830SE does 

not affect the ability to accomplish the 

actions required by this final rule. 

Therefore, for airplanes on which STC 

ST00830SE is installed, a ‘‘change in 

product’’ Alternative Method of 

Compliance (AMOC) approval request is 

not necessary to comply with the 

requirements of 14 CFR 39.17. 

Request To Revise Compliance Time 

The European Aviation Safety Agency 

(EASA) noted that Boeing Alert Service 

Bulletin 737–53A1352, dated October 2, 

2015, specifies that the existing 737– 

600/700/800/900 Maintenance Planning 

Document (MPD), Section 9, 

Airworthiness Limitation Instruction 

(ALI) Inspection Program, is not 

sufficient to prevent WFD in the S–14L 

and S–14R lap splice, lower fastener 

rows, between station (STA) 360–540 

and STA 727–887, as the airplane ages. 

EASA added that this service 

information specifies inspections at 

principal structural elements (PSEs) 53– 

30–04–6, 53–30–04–6a, 53–60–04–6 and 

53–60–04–6a before accumulating 

54,000 total flight cycles. However, 

EASA noted that 737–600/700/800/900 

MPD, Section 9, C626AOO 1–CMR 

Table 9–2, Revision August 2012, 

requires doing the inspections before 

accumulating 50,000 flight cycles; 

which contradicts the initial statement 

that the ALI inspection program is not 

sufficient to preclude WFD. EASA 

concluded that if the current ALI is not 

sufficient to preclude WFD, then the 

50,000 flight cycles should be reduced, 

rather than increased to 54,000 flight 

cycles. 

We infer the commenter is requesting 

that we reduce the 54,000 flight-cycle 

compliance time specified in Boeing 

Alert Service Bulletin 737–53A1352, 

Revision 1, dated March 10, 2016 

(which is the appropriate source of 

service information for accomplishing 

the required actions in this AD). We do 

not agree with the request to reduce the 

compliance time. However, we do agree 

to clarify the WFD analysis. Boeing uses 

a different methodology than the 

standard damage tolerance analysis for 

evaluating structure that is susceptible 

to WFD. This methodology can 

sometimes produce a longer initial 

inspection threshold than the baseline 

maintenance program, but requires more 

frequent repetitive inspections, as in the 

case of the S–14L and S–14R lap splices. 

Although, for certain airplanes, the 

initial WFD threshold specified in 

Boeing Alert Service Bulletin 737– 

53A1352, Revision 1, dated March 10, 

2016, is 4,000 flight cycles more than 

the ALI threshold; the repetitive 

inspection interval is reduced by 6,000 

flight cycles. 

Operators are still required to 

accomplish the ALI inspections in 

accordance with 14 CFR 91.403(c). 

However, if the inspections specified in 

Boeing Alert Service Bulletin 737– 

53A1352, Revision 1, dated March 10, 

2016, and the ALI inspections overlap 

(same location, inspection detail, and 

technique) then the more restrictive of 

the two programs satisfies both 

requirements. Since a specific revision 

of the ALI inspections are required by 

AD 2013–19–23, Amendment 39–17605 

(78 FR 61173, October 3, 2013), Boeing 

Alert Service Bulletin 737–53A1352, 

Revision 1, dated March 10, 2016, 

contains an approved AMOC to AD 

2013–19–23, for certain PSEs, after the 

initial inspections in that service 

bulletin are accomplished. We have not 

changed this AD in this regard. 

Request for Clarification of Extent of 

Boeing Organization Designation 

Authorization (ODA) 

Southwest Airlines (SWA) asked for 

clarification that the Boeing ODA 

identified in paragraph (i)(3) of the 

proposed AD can provide an AMOC for 

any ‘‘repair, modification, or alteration’’ 

that includes the authority to approve 

existing repairs in the inspection area 

that inhibit accomplishment of the AD 

requirements as terminating action to 

paragraph (g) of the proposed AD. SWA 

also asked if the ODA has the authority 

to provide alternative inspection 

procedures for repaired areas where the 

inspection in paragraph (g) of the 

proposed AD cannot be accomplished. 

Additionally, SWA asked that we clarify 

that the Boeing ODA identified in 

paragraph (i)(3) of the proposed AD is 

able to issue an AMOC for an existing 

repair at the S–14 lap joint (where the 

location of the repair inhibits 

accomplishing the initial inspection), 

provided the repair was approved by 

any FAA designation authority and 

there are a minimum of three fastener 

rows above and below the lap joint. 

SWA stated that neither Boeing Alert 

Service Bulletin 737–53A1352, dated 

October 2, 2015, nor the NPRM clearly 

state how to address existing repairs 

that prevent accomplishment of the 

inspections specified in paragraph (g) of 

the proposed AD. 

We agree with the commenter that 

clarification of the extent of the 

authority of the Boeing ODA is 

necessary. The Boeing ODA includes 

the authority to evaluate existing repairs 

and provide alternative inspection 

programs in the repaired area, and 

includes approval of alternative 

inspections as AMOCs if 

accomplishment of the inspections 

required by paragraph (g) of this AD is 

inhibited. We have not changed this AD 

in this regard. 


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We infer that SWA is asking if the 

Boeing ODA can issue a global AMOC 

for the referenced repair. The Boeing 

ODA does not have that authority. We 

have not received any information from 

Boeing that defines such a repair that 

would be considered for a global 

AMOC. If Boeing provides supporting 

data, we will evaluate the data to 

determine if that repair and any 

associated inspections provide an 

acceptable level of safety. We have not 

changed this AD in this regard. 

Change to This AD 

We have reviewed Boeing Alert 

Service Bulletin 737–53A1352, Revision 

1, dated March 10, 2016, and there are 

no substantial changes. Therefore, we 

have included Boeing Alert Service 

Bulletin 737–53A1352, Revision 1, 

dated March 10, 2016, as the 

appropriate source of service 

information for accomplishing in the 

actions required by paragraph (g) of this 

AD. We have also added a new 

paragraph (h) to this AD to provide 

credit for actions done prior to the 

effective date of this AD using Boeing 

Alert Service Bulletin 737–53A1352, 

dated October 2, 2015. We have 

redesignated subsequent paragraphs 

accordingly. 

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 Boeing Alert Service 

Bulletin 737–53A1352, Revision 1, 

dated March 10, 2016. The service 

information describes procedures for 

low frequency eddy current inspections 

and repair for cracking in the lower 

fastener row of the S–14L and S–14R lap 

splices. 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 1,513 

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 

Inspection for Group 1 airplanes 

(1,471 airplanes).

84 work-hours × $85 per hour = 

$7,140 per inspection cycle.

$0 $7,140 per inspection 

cycle.

$10,502,940 per inspection cycle. 

Inspection for Group 2 airplanes 

(42 airplanes).

65 work-hours × $85 per hour = 

$5,525 per inspection cycle.

0 $5,525 per inspection 

cycle.

$232,050 per inspection 

cycle. 

We have received no definitive data 

that enables us to provide cost estimates 

for the on-condition actions specified in 

this AD. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. Subtitle VII: 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701: 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

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 adding 

the following new airworthiness 

directive (AD): 

2016–22–13 The Boeing Company: 

Amendment 39–18702; Docket No. 

FAA–2016–5034; Directorate Identifier 

2015–NM–172–AD. 

(a) Effective Date 

This AD is effective December 27, 2016. 

(b) Affected ADs 

None. 

(c) Applicability 

(1) This AD applies to all The Boeing 

Company Model 737–600, –700, –700C, 

–800, –900, and –900ER series airplanes, 

certificated in any category. 

(2) Installation of Supplemental Type 

Certificate (STC) ST00830SE (http://

rgl.faa.gov/Regulatory_and_Guidance_

Library/rgSTC.nsf/0/38B606833BBD98B386

257FAA00602538?OpenDocument&Highlight

=st00830se) does not affect the ability to 

accomplish the actions required by this AD. 

Therefore, for airplanes on which STC 


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ST00830SE is installed, a ‘‘change in 

product’’ alternative method of compliance 

(AMOC) approval request is not necessary to 

comply with the requirements of 14 CFR 

39.17. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by an evaluation by 

the design approval holder (DAH) indicating 

that the stringer (S)–14L and S–14R lap 

splices are subject to widespread fatigue 

damage (WFD). We are issuing this AD to 

detect and correct widespread cracking in the 

S–14L and S–14R lap splices that could 

rapidly link up and result in possible rapid 

decompression and reduced structural 

integrity of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Inspections 

At the applicable compliance time 

specified in paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 737–53A1352, 

Revision 1, dated March 10, 2016, do a low 

frequency eddy current inspection for 

cracking of the lower fastener row of S–14L 

and S–14R lap splices, in accordance with 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin 737–53A1352, 

Revision 1, dated March 10, 2016. Repeat the 

inspection thereafter at the applicable times 

specified in paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 737–53A1352, 

Revision 1, dated March 10, 2016. If any 

cracking is found, before further flight, repair 

using a method approved in accordance with 

the procedures specified in paragraph (i) of 

this AD. 

(h) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraph (g) of this AD, 

if those actions were performed before the 

effective date of this AD using Boeing Alert 

Service Bulletin 737–53A1352, dated October 

2, 2015. 

(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) 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. If a step or substep is 

labeled ‘‘RC Exempt,’’ then the RC 

requirement is removed from that step or 

substep. 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 

For more information about this AD, 

contact Gaetano Settineri, Aerospace 

Engineer, Airframe Branch, ANM–120S, 

FAA, Seattle ACO, 1601 Lind Avenue SW., 

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

6577; fax: 425–917–6590; email: 

gaetano.settineri@faa.gov. 

(k) 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. 

(i) Boeing Alert Service Bulletin 737– 

53A1352, Revision 1, dated March 10, 2016. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Contractual & Data 

Services (C&DS), 2600 Westminster Blvd., 

MC 110–SK57, Seal Beach, CA 90740; 

telephone 562–797–1717; Internet https://

www.myboeingfleet.com. 

(4) 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. 

(5) 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 October 

21, 2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–26621 Filed 11–21–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–3820; Directorate 

Identifier 2014–SW–024–AD; Amendment 

39–18716; AD 2016–23–09] 

RIN 2120–AA64 

Airworthiness Directives; Various 

Restricted Category Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for various 

restricted category helicopters. This AD 

requires cleaning and visually 

inspecting certain main rotor (M/R) 

blades and, depending on the outcome 

of the inspections, repairing or replacing 

the M/R blades. This AD was prompted 

by a report of an M/R blade with 

multiple fatigue cracks around the blade 

retention bolt hole. The actions are 

intended to detect a crack in the M/R 

blade, and prevent failure of the M/R 

blade and subsequent loss of helicopter 

control. 

DATES: This AD is effective December 

27, 2016. 

ADDRESSES: For service information 

identified in this final rule, contact Bell 

Helicopter Textron, Inc., P.O. Box 482, 

Fort Worth, TX 76101; telephone (817) 

280–3391; fax (817) 280–6466; or at 

http://www.bellcustomer.com/files/. 

You may review a copy of the 

referenced service information at the 

FAA, Office of the Regional Counsel, 

Southwest Region, 10101 Hillwood 

Pkwy, Room 6N–321, Fort Worth, TX 

76177. 

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–2015– 

3820; or in person at the Docket 

Operations Office between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. The AD docket 

contains this AD, the economic 

evaluation, any comments received, and 

other information. The street address for 


sradovich on DSK3GMQ082PROD with RULES