Federal Register / Vol. 82, No. 183 / Friday, September 22, 2017 / Rules and Regulations 44301 

This unsafe condition, if not corrected, could 

result in failure of the HPC impeller, 

uncontained HPC impeller release, damage to 

the engine, and damage to the airplane/ 

helicopter. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) For CT7–9B engines, remove the 

affected HPC impeller from service at the 

next engine shop visit after the effective date 

of this AD, or prior to accumulating 12,000 

cycles since new, whichever is earlier. 

(2) For CT7–8A engines, remove the 

affected HPC impeller from service at the 

next engine shop visit after the effective date 

of this AD, or prior to accumulating 1,500 

engine hours after the effective date of this 

AD, whichever is earlier. 

(g) Definition 

For the purpose of this AD, an ‘‘engine 

shop visit’’ is the induction of an engine into 

the shop for maintenance involving the 

separation of pairs of major mating engine 

flanges. 

(h) 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. 

(i) Related Information 

(1) For more information about this AD, 

contact Kasra Sharifi, Aerospace Engineer, 

ECO Branch, FAA, 1200 District Avenue, 

Burlington, MA 01803; phone: 781–238– 

7773; fax: 781–238–7199; email: 

kasra.sharifi@faa.gov. 

(2) GE Service Bulletin CT7–TP S/B 72– 

0524, dated June 16, 2016, can be obtained 

from GE using the contact information in 

paragraph (i)(3) of this AD. 

(3) For service information identified in 

this AD, contact General Electric Company, 

GE–Aviation, Room 285, 1 Neumann Way, 

Cincinnati, OH 45215; phone: 513–552–3272; 

fax: 513–552–3329; email: geae.aoc@ge.com. 

(4) You may view this service information 

at the FAA, Engine and Propeller Standards 

Branch, 1200 District Avenue, Burlington, 

MA 01803. For information on the 

availability of this material at the FAA, call 

781–238–7125. 

(j) Material Incorporated by Reference 

None. 

Issued in Burlington, Massachusetts, on 

September 13, 2017. 

Robert J. Ganley, 

Manager, Engine and Propeller Standards 

Branch, Aircraft Certification Service. 

[FR Doc. 2017–19961 Filed 9–21–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–9185; Product 

Identifier 2016–NM–077–AD; Amendment 

39–19040; AD 2017–19–10] 

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 certain 

The Boeing Company Model 757–200, 

–200PF, and –200CB series airplanes. 

This AD was prompted by an analysis 

of the cam support assemblies of the 

main cargo door (MCD) that indicated 

that the existing maintenance program 

for the cam support assemblies is not 

adequate to reliably detect cracks before 

two adjacent cam support assemblies 

could fail. This AD requires an 

inspection to determine part numbers, 

repetitive inspections to detect cracking 

of affected cam support assemblies of 

the MCD, and replacement if necessary. 

We are issuing this AD to address the 

unsafe condition on these products. 

DATES: This AD is effective October 27, 

2017. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of October 27, 2017. 

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 90740–5600; 

telephone 562–797–1717; Internet 

https://www.myboeingfleet.com. You 

may view this service information at the 

FAA, Transport Standards Branch, 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– 

9185. 

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– 

9185; 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 final rule, 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: 

Chandra Ramdoss, Aerospace Engineer, 

Airframe Section, FAA, Los Angeles 

ACO Branch, 3960 Paramount 

Boulevard, Lakewood, CA 90712–4137; 

phone: 562–627–5239; fax: 562–627– 

5210; email: chandraduth.ramdoss@

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 

757–200, –200PF, and –200CB series 

airplanes. The NPRM published in the 

Federal Register on October 4, 2016 (81 

FR 68371) (‘‘the NPRM’’). The NPRM 

was prompted by an analysis of the cam 

support assemblies of the MCD that 

indicated that the existing maintenance 

program for the cam support assemblies 

is not adequate to reliably detect cracks 

before two adjacent cam support 

assemblies could fail. The NPRM 

proposed to require an inspection to 

determine part numbers, repetitive 

inspections to detect cracking of 

affected cam support assemblies of the 

MCD, and replacement if necessary. We 

are issuing this AD to detect and correct 

cracking of the cam support assemblies 

of the MCD, which could result in 

reduced structural integrity of the MCD 

and consequent rapid decompression of 

the airplane. 

Comments 

We gave the public the opportunity to 

participate in developing this final rule. 

The following presents the comments 

received on the NPRM and the FAA’s 

response to each comment. 

Requests To Revise Applicability 

Boeing, Delta Air Lines (DAL), 

European Air Transport Leipzig GmbH 

(EAT), DHL Express (DHL), FedEx 

Express (FedEx), and United Airlines 

(UAL) requested that we revise the 

proposed AD applicability. DAL and 

UAL requested that airplanes that do 

not have a MCD be excluded from the 

AD applicability. 

Three of these commenters requested 

that the actions of the service 

information be applicable only to 

44302 Federal Register / Vol. 82, No. 183 / Friday, September 22, 2017 / Rules and Regulations 

airplanes in the service information 

effectivity. These commenters explained 

that the service information effectivity 

includes only airplanes that have a MCD 

installed by Boeing, either as a Boeing 

factory-delivered freighter or as a Boeing 

Supplemental Type Certificate (STC)- 

converted freighter, and not airplanes 

that have been converted to a freighter 

by a non-Boeing STC. 

EAT and DHL requested that we 

revise the applicability of the proposed 

AD to exclude Model 757 airplanes with 

passenger to freighter modification STC 

ST01529SE by Precision Conversions. 

FedEx requested that we either 

withdraw the NPRM and issue a new 

one, to include a separate section for 

airplanes modified under VT Mobile 

Aerospace Engineering STC 

ST03562AT, or exempt the airplanes 

modified by that STC from the NPRM 

and issue a new NPRM for airplanes 

modified by that STC. FedEx also 

requested that we revise the NPRM to 

mandate, for Model 757–200 airplanes 

modified in accordance with STC 

ST03562AT, VT Mobile Aerospace 

Engineering Service Bulletin 

MAE757SF–SB–52–l 601, Revision 0, 

dated April 15, 2016, or a subsequent 

revision, instead of Boeing Alert Service 

Bulletin 757–52A0094, dated December 

23, 2015. FedEx explained that the MCD 

that is installed by the Precision 

Conversion STC is different than that 

installed by Boeing or VT Mobile 

Aerospace Engineering and does not 

have the affected cam support fittings 

installed. FedEx stated that it prefers the 

VT Mobile Aerospace Engineering 

service information for modifying 

airplanes instead of the Boeing service 

information, since Boeing does not 

provide support for the VT Mobile 

Aerospace STC, and any discrepancies 

or questions on the Boeing service 

information would be addressed by 

Boeing based on goodwill, rather than 

by contractual agreement. 

We partially agree with the 

commenters’ requests. We agree that the 

unsafe condition does not apply to 

Model 757–200 airplanes that do not 

have a MCD and to airplanes modified 

from passenger to freighter in 

accordance with Precision Conversions 

STC ST01529SE. The unsafe condition 

applies only to MCD cam support 

assemblies with the specified part 

numbers. 

We disagree that the AD should apply 

only to Boeing converted freighters. We 

also disagree that a separate AD should 

be issued to address Model 757–200 

freighters modified by STC ST03562AT 

or any of the other passenger-to-freighter 

modification STCs because these 

support assemblies having affected part 

numbers could be installed during 

original aircraft manufacture, or during 

passenger-to-freighter modification. The 

unsafe condition applies only to 

airplanes with certain part number cam 

support assemblies installed, and it does 

not apply to Model 757–200 airplanes 

that do not have a MCD. 

Paragraphs (g) and (h) of this AD list 

the part numbers of the cam support 

assemblies that have the unsafe 

condition. We have confirmed that the 

cam support assemblies having affected 

part numbers are not installed on Model 

757 airplanes as part of the Precision 

Conversions STC ST01529SE passengerto-freighter conversion. We have revised 

the SUMMARY section, Discussion 

section, and paragraph (c) of this AD to 

state that the AD applies to all Model 

757–200, –200PF, and –200CB series 

airplanes equipped with a MCD, except 

those airplanes that have been 

converted from a passenger to freighter 

configuration in accordance with STC 

ST01529SE. 

We expect that the actions specified 

in Boeing Alert Service Bulletin 757– 

52A0094, Revision 2, dated May 2, 2017 

(‘‘ASB 757–52A0094, R2’’), can be 

accomplished on airplanes that are not 

identified in that service information. In 

addition, we do not consider it 

appropriate to include various 

provisions in an AD applicable only to 

an operator’s unique configuration of 

affected airplanes. However, if an 

operator with a Model 757–200 freighter 

cannot accomplish the required actions 

specified in the service information, or 

prefers to use different service 

information that is specific to their 

design (such as FedEx’s request to use 

VT Mobile Aerospace Engineering 

Service Bulletin MAE757SF–SB–52–l 

601, Revision 0, dated April 15, 2016), 

an alternative method of compliance 

(AMOC) can be requested in accordance 

with paragraph (j) of this AD. 

Requests To Revise the Compliance 

Time 

Boeing and FedEx requested that we 

revise the compliance time in paragraph 

(g)(l) of the proposed AD from ‘‘18,000 

total flight cycles’’ to ‘‘18,000 door flight 

cycles.’’ The commenters explained that 

some of the affected airplanes have been 

converted from passenger to freighter 

airplanes, and for these converted 

airplanes, the cam support assemblies 

were installed at the time of the aircraft 

conversion, not when the airplanes were 

produced. The commenters stated that, 

for these converted airplanes, the initial 

compliance time for inspection should 

be based on the number of flight cycles 

since the part has been installed. In 

addition, Boeing stated that ASB 757– 

52A0094, R2, was revised to change the 

inspection threshold for Boeing 

converted freighter airplanes to total 

flight cycles after freighter conversion 

redelivery. 

We agree with the commenters’ 

request. For airplanes that have been 

converted to freighters, the compliance 

time for the initial inspection should be 

based on the number of cycles the cam 

support assembly has been in service. 

We have revised paragraph (g)(1) of this 

AD accordingly. 

Request To Withdraw the NPRM and 

Reference Revised Service Information 

FedEx requested that we withdraw 

the NPRM and issue a new NPRM to 

require compliance with ASB 757– 

52A0094, R2, instead of Boeing Alert 

Service Bulletin 757–52A0094, dated 

December 23, 2015. 

We partially agree with the 

commenter’s request. We agree with the 

commenter’s request to reference ASB 

757–52A0094, R2, as the appropriate 

source of service information. Revision 

1 of Boeing Alert Service Bulletin 757– 

52A0094, dated April 21, 2016 (‘‘ASB 

757–52A0094, R1’’), removed one 

airplane from the effectivity and 

updated some references and 

publications affected. ASB 757– 

52A0094, R2, removed non-Boeing-STCconverted freighter airplanes from the 

effectivity and changed the initial 

compliance time for the converted 

freighter airplanes to flight cycles after 

freighter conversion redelivery. 

We disagree with withdrawing the 

NPRM and reissuing a new NPRM 

requiring compliance with ASB 757– 

52A0094, R2, because doing so would 

unnecessarily delay issuance of the final 

rule. Additionally, the compliance time 

can be corrected in the final rule 

without the need for a supplemental 

NPRM since the corrected compliance 

time will provide additional time for the 

converted freighter airplanes and will 

not reduce the initial compliance time 

for any airplane. We have revised this 

AD to refer to ASB 757–52A0094, R2, as 

the appropriate source of service 

information. We have also added 

paragraph (i) to this AD to provide 

credit for actions required by paragraph 

(h) of this AD, if those actions were 

performed before the effective date of 

this AD using Boeing Alert Service 

Bulletin 757–52A0094, dated December 

23, 2015; or ASB 757–52A0094, R1. We 

have redesignated subsequent 

paragraphs accordingly. 

Request To Correct Manual Reference 

in the Service Information 

United Parcel Service (UPS) requested 

that we revise paragraph (h) of the 

Federal Register / Vol. 82, No. 183 / Friday, September 22, 2017 / Rules and Regulations 44303 

proposed AD to specify use of Airplane 

Maintenance Manual (AMM) 52–32–11 

in lieu of Component Maintenance 

Manual (CMM) 52–32–03 for the cam 

and bell-crank assembly installation. 

UPS explained that Boeing Alert Service 

Bulletin 757–52A0094, dated December 

23, 2015, included an incorrect manual 

reference. 

We partially agree with the 

commenter’s request. We agree that the 

manual reference is incorrect in Boeing 

Alert Service Bulletin 757–52A0094, 

dated December 23, 2015. The incorrect 

reference was changed in ASB 757– 

52A0094, R2, and, as explained 

previously, ASB 757–52A0094, R2, is 

referenced as the appropriate source of 

service information in this AD. No 

further change is necessary 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 

final rule 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 final rule. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Boeing Alert Service 

Bulletin 757–52A0094, Revision 2, 

dated May 2, 2017. This service 

information describes procedures for an 

ultrasonic inspection of the cam support 

assemblies of the main cargo door, and 

replacement of the cam support 

assemblies. 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 will affect 

212 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 ........ 6 work-hours × $85 per hour = $510 

per inspection cycle.

$0 $510 per inspection cycle .......... $108,120 per inspection cycle. 

We estimate the following costs to do 

any necessary replacements 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 replacements: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Replacement (per pair of cam support assemblies) .... 60 work-hours × $85 per hour = $5,100 ...................... $15,298 $20,398 

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. 

This AD is issued in accordance with 

authority delegated by the Executive 

Director, Aircraft Certification Service, 

as authorized by FAA Order 8000.51C. 

In accordance with that order, issuance 

of ADs is normally a function of the 

Compliance and Airworthiness 

Division, but during this transition 

period, the Executive Director has 

delegated the authority to issue ADs 

applicable to transport category 

airplanes to the Director of the System 

Oversight Division. 

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: 

44304 Federal Register / Vol. 82, No. 183 / Friday, September 22, 2017 / Rules and Regulations 

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): 

2017–19–10 The Boeing Company: 

Amendment 39–19040; Docket No. 

FAA–2016–9185; Product Identifier 

2016–NM–077–AD. 

(a) Effective Date 

This AD is effective October 27, 2017. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 757–200, –200PF, and –200CB series 

airplanes, certificated in any category, 

equipped with a main cargo door (MCD), 

except those airplanes that have been 

converted from a passenger to freighter 

configuration in accordance with 

Supplemental Type Certificate ST01529SE 

(http://rgl.faa.gov/Regulatory_and_

Guidance_Library/rgstc.nsf/0/9c0283b6

ce0b9ff18625806b007340b9/$FILE/ 

ST01529SE.pdf). 

(d) Subject 

Air Transport Association (ATA) of 

America Code 52, Doors. 

(e) Unsafe Condition 

This AD was prompted by an analysis of 

the cam support assemblies of the MCD that 

indicated that the existing maintenance 

program for the cam support assemblies is 

not adequate to reliably detect cracks before 

two adjacent cam support assemblies could 

fail. We are issuing this AD to detect and 

correct cracking of the cam support 

assemblies of the MCD, which could result in 

reduced structural integrity of the MCD and 

consequent rapid decompression of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection To Determine Part Numbers 

At the later of the times specified in 

paragraphs (g)(1) and (g)(2) of this AD: 

Inspect the cam support assemblies of the 

MCD to determine whether part number (P/ 

N) 69–23588–5, 69–23588–6, 69–23588–7, 

69–23588–8, 69–23588–9, or 69–23588–10 is 

installed. A review of airplane maintenance 

records is acceptable in lieu of this 

inspection if the part number(s) of the cam 

support assemblies of the MCD can be 

conclusively determined from that review. 

(1) Before the accumulation of 18,000 total 

flight cycles since installation of the MCD. If 

the flight cycles since installation of the MCD 

are not known, use total airplane flight 

cycles. 

(2) Within 2,743 flight cycles or 27 months 

after the effective date of this AD, whichever 

occurs later. 

(h) Inspections and Corrective Actions 

If, during the inspection required by 

paragraph (g) of this AD, any cam support 

assembly of the MCD having P/N 69–23588– 

5, 69–23588–6, 69–23588–7, 69–23588–8, 

69–23588–9, or 69–23588–10 is determined 

to be installed: At the later of the times 

specified in paragraphs (g)(1) and (g)(2) of 

this AD, do an ultrasonic inspection to detect 

cracking of the affected cam support 

assemblies of the MCD; and do all applicable 

replacements; in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 757–52A0094, Revision 2, 

dated May 2, 2017. Do all applicable 

replacements before further flight. Repeat the 

inspection thereafter at intervals not to 

exceed 6,000 flight cycles. Replacement of a 

cam support assembly of the MCD does not 

terminate the repetitive inspections required 

by this paragraph. 

(i) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraph (h) of this AD, if those 

actions were performed before the effective 

date of this AD using Boeing Alert Service 

Bulletin 757–52A0094, dated December 23, 

2015; or Boeing Alert Service Bulletin 757– 

52A0094, Revision 1, dated April 21, 2016. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Los Angeles ACO Branch, 

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 

certification office, send it to the attention of 

the person identified in paragraph (k)(1) of 

this AD. Information may be emailed to: 

9-ANM-LAACO-AMOC-Requests@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, Los Angeles 

ACO Branch, 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 (j)(4)(i) and (j)(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. 

(k) Related Information 

(1) For more information about this AD, 

contact Chandra Ramdoss, Aerospace 

Engineer, Airframe Section, FAA, Los 

Angeles ACO Branch, 3960 Paramount 

Boulevard, Lakewood, CA 90712–4137; 

phone: 562–627–5239; fax: 562–627–5210; 

email: chandraduth.ramdoss@faa.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (l)(3) and (l)(4) of this AD. 

(l) 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 757– 

52A0094, Revision 2, dated May 2, 2017. 

(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 90740–5600; 

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

www.myboeingfleet.com. 

(4) You may view this service information 

at the FAA, Transport Standards Branch, 

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 

September 7, 2017. 

Jeffrey E. Duven, 

Director, System Oversight Division, Aircraft 

Certification Service. 

[FR Doc. 2017–19767 Filed 9–21–17; 8:45 am] 

BILLING CODE 4910–13–P