Federal Register / Vol. 82, No. 165 / Monday, August 28, 2017 / Rules and Regulations 40683 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Rolls-Royce plc (RR) 

Trent XWB–75, Trent XWB–79, Trent XWB– 

79B, and Trent XWB–84 turbofan engines 

with an engine serial number (S/N) listed in 

Appendix 1 of RR Alert Non-Modification 

Service Bulletin (NMSB) Trent XWB 72– 

AJ738, dated April 11, 2017, and with 

intermediate-pressure (IP) turbine stage 2 

locking plates, part number (P/N) KH12922 

or KH16183, installed. 

(d) Subject 

Joint Aircraft System Component (JASC) 

7250, Turbine/Turboprop Engine/Turbine 

Section. 

(e) Reason 

This AD was prompted by a report of 

several IP turbine stage 2 locking plates 

cracked during module assembly. We are 

issuing this AD to prevent failure of the IP 

turbine stage 2 locking plates, uncontained 

release of the IP turbine stage 2 blades, 

damage to the engine, and damage to the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) Inspect the IP turbine stage 2 locking 

plates on-wing before exceeding 750 engine 

flight cycles (FCs) since new, or within 100 

engine FCs after the effective date of this AD, 

whichever occurs later. Use the 

Accomplishment Instructions, paragraph 

3.A., of RR Alert NMSB Trent XWB 72– 

AJ738, dated April 11, 2017, to do the 

inspection. 

(2) Thereafter, re-inspect the IP turbine 

stage 2 locking plates at intervals not to 

exceed 750 engine FCs since the last locking 

plate inspection. Use the Accomplishment 

Instructions, paragraph 3.A., of RR Alert 

NMSB Trent XWB 72–AJ738, dated April 11, 

2017, to do the inspection. 

(i) If all IP turbine stage 2 locking plates 

installed on the engine have an S/N 

beginning with 20452, or are not marked 

with an S/N, the repetitive inspection 

required by paragraph (f)(2) of this AD is not 

required. 

(ii) If one or more IP turbine stage 2 locking 

plates are missing, remove the engine from 

service within the compliance times 

specified in the Accomplishment 

Instructions, paragraph 3.A.(3), of RR Alert 

NMSB Trent XWB 72–AJ738, dated April 11, 

2017. 

(3) Inspect the IP turbine stage 2 locking 

plates during the next engine shop visit 

(ESV) after the effective date of this AD. 

(i) Use the Accomplishment Instructions, 

paragraph 3.B., of RR Alert NMSB Trent 

XWB 72–AJ738, dated April 11, 2017, to do 

this inspection. This in-shop inspection may 

be substituted for the on-wing inspection 

required by paragraphs (f)(1) and (2) of this 

AD. 

(ii) If one or more IP turbine stage 2 locking 

plates are missing, use the acceptance criteria 

in the Accomplishment Instructions, 

paragraph 3.B.(3), of RR Alert NMSB Trent 

XWB 72–AJ738 dated April 11, 2017, to 

disposition the engine. 

(g) Installation Prohibition 

After the effective date of this AD, do not 

install an engine unless the IP turbine stage 

2 locking plates were inspected using the 

Accomplishment Instructions, paragraph 3.A. 

or 3.B., of RR Alert NMSB Trent XWB 72– 

AJ738, dated April 11, 2017. 

(h) Definition 

For the purpose of this AD, an ESV is when 

the engine is subject to a serviceability check 

and repair, rebuild, or overhaul. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, FAA, ECO Branch, 

Compliance and Airworthiness Division, 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. 

(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. 

(j) Related Information 

(1) For more information about this AD, 

contact Robert Green, Aerospace Engineer, 

FAA, ECO Branch, Compliance and 

Airworthiness Division, 1200 District 

Avenue, Burlington, MA 01803; phone: 781– 

238–7754; fax: 781–238–7199; email: 

robert.green@faa.gov. 

(2) Refer to MCAI European Aviation 

Safety Agency AD 2017–0088, dated May 16, 

2017, 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–2017–0642. 

(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) Rolls-Royce plc (RR) Alert NonModification Service Bulletin Trent XWB 72– 

AJ738, dated April 11, 2017. 

(ii) Reserved. 

(3) For RR service information identified in 

this AD, contact Rolls-Royce plc, Corporate 

Communications, P.O. Box 31, Derby, 

England, DE24 8BJ; phone: 011–44–1332– 

242424; fax: 011–44–1332–249936; email: 

http://www.rolls-royce.com/contact/civil_

team.jsp; Internet: https://customers.rollsroyce.com/public/rollsroycecare. 

(4) You may view this service information 

at FAA, Engine and Propeller Standards 

Branch, Policy and Innovation Division, 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 

August 16, 2017. 

Robert J. Ganley, 

Manager, Engine and Propeller Standards 

Branch, Aircraft Certification Service. 

[FR Doc. 2017–18133 Filed 8–25–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–0472; Product 

Identifier 2016–NM–148–AD; Amendment 

39–19002; AD 2017–17–12] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Airbus Model A310–203, –221, –222, 

–304, –322, –324, and –325 airplanes. 

This AD was prompted by an evaluation 

by the design approval holder indicating 

that the wing bottom skin at the main 

landing gear (MLG) reinforcing plate is 

subject to widespread fatigue damage 

(WFD). This AD requires a modification 

of the wing bottom skin at the MLG 

reinforcing plate. We are issuing this AD 

to address the unsafe condition on these 

products. 

DATES: This AD is effective October 2, 

2017. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of October 2, 2017. 

ADDRESSES: For service information 

identified in this final rule, contact 

Airbus SAS, Airworthiness Office— 

EAW, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone 

+33 5 61 93 36 96; fax +33 5 61 93 44 

51; email account.airworth-eas@

airbus.com; Internet http://

www.airbus.com. You may view this 

referenced 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–2017– 

0472. 


asabaliauskas on DSKBBXCHB2PROD with RULES
40684 Federal Register / Vol. 82, No. 165 / Monday, August 28, 2017 / Rules and Regulations 

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–2017– 

0472; 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: Dan 

Rodina, Aerospace Engineer, 

International Section, Transport 

Standards Branch, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–2125; fax 425–227– 

1149. 

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 Airbus Model A310–203, 

–221, –222, –304, –322, -324, and -325 

airplanes. The NPRM published in the 

Federal Register on May 19, 2017 (82 

FR 22904) (‘‘the NPRM’’). The NPRM 

was prompted by an evaluation by the 

design approval holder indicating that 

the wing bottom skin at the MLG 

reinforcing plate is subject to WFD. The 

NPRM proposed to require a 

modification of the wing bottom skin at 

the MLG reinforcing plate. We are 

issuing this AD to prevent multi-site 

damage in the bottom skin at the MLG 

reinforcing plate, which could result in 

reduced structural integrity of the wing. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2016–0170, dated August 19, 

2016 (referred to after this as the 

Mandatory Continuing Airworthiness 

Information, or ‘‘the MCAI’’), to correct 

an unsafe condition for all Airbus 

Model A310–203, –221, –222, –304, 

–322, –324, and –325 airplanes. The 

MCAI states: 

In response to the FAA Part 26 rule, wing 

structural items of the Airbus A310 design 

that are deemed potentially susceptible to 

Widespread Fatigue Damage (WFD) have 

been assessed. The bottom skin at the main 

landing gear (MLG) reinforcing plate has 

been highlighted as an area susceptible to 

Multi Site Damage (MSD). 

This condition, if not corrected, could 

reduce the structural integrity of the wing. 

Airbus performed a detailed widespread 

fatigue damage tolerance analysis of the 

bottom skin at the MLG reinforcing plate, and 

concluded that a modification is necessary to 

the fastener holes at the inboard edge of the 

reinforcing plate forward of the rear spar. The 

modification consists of inspection [related 

investigative actions of a check and a rotating 

probe inspection] and a first oversize of the 

critical holes on the first two rows of 

fasteners [and corrective actions, e.g., repair]. 

Airbus modification 13751 was introduced 

and Service Bulletin (SB) A310–57–2104 was 

issued to provide in-service modification 

instructions. The accomplishment of this 

modification at the specified time will 

recondition/renovate/extend the life of the 

fastener holes in the bottom skin at the MLG 

reinforcing plate and prevent the 

development of MSD up to the Extended 

Service Goal (ESG). 

For the reasons described above, this 

[EASA] AD requires certain modifications to 

the wing bottom skin at the MLG reinforcing 

plate, forward of the wing rear spar 

[including related investigative actions of a 

check and a rotating probe inspection and 

corrective actions, e.g., repair]. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2017– 

0472. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting this AD 

as proposed except for 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. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued Service Bulletin 

A310–57–2104, dated December 15, 

2015. This service information describes 

procedures for modification of the lefthand and right-hand wing bottom skin 

at the MLG reinforcing plate, including 

related investigative actions and 

applicable corrective actions. 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 8 

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 

Modification ............................. 52 work-hours × $85 per hour = $4,420 ................................ $12,000 $16,420 $131,360 

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 


asabaliauskas on DSKBBXCHB2PROD with RULES
Federal Register / Vol. 82, No. 165 / Monday, August 28, 2017 / Rules and Regulations 40685 

applicable to transport category 

airplanes to the Director of the System 

Oversight Division. 

Regulatory Findings 

We 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 the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska; and 

4. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

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): 

2017–17–12 Airbus: Amendment 39–19002; 

Docket No. FAA–2017–0472; Product 

Identifier 2016–NM–148–AD. 

(a) Effective Date 

This AD is effective October 2, 2017. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Model A310– 

203, –221, –222, –304, –322, –324, and –325 

airplanes, certificated in any category, all 

manufacturer serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Reason 

This AD was prompted by an evaluation by 

the design approval holder indicating that 

the wing bottom skin at the main landing 

gear (MLG) reinforcing plate is subject to 

widespread fatigue damage. We are issuing 

this AD to prevent multi-site damage in the 

bottom skin at the MLG reinforcing plate, 

which could result in reduced structural 

integrity of the wing. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Modification 

Within the compliance times defined in 

table 1 to paragraph (g) of this AD, table 2 

to paragraph (g) of this AD, or table 3 to 

paragraph (g) of this AD, as applicable to 

airplane type and utilization: Do a 

modification of the left-hand and right-hand 

wing bottom skin at the MLG reinforcing 

plate, including all related investigative 

actions and applicable corrective actions, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A310– 

57–2104, dated December 15, 2015, except as 

required by paragraph (h) of this AD. Do all 

related investigative and applicable 

corrective actions before further flight. For 

the purpose of this AD, the term ‘‘short 

range’’ applies to airplanes with an average 

flight time (AFT) lower than 1.5 flight hours 

per flight cycle, and the term ‘‘long range’’ 

applies to airplanes with an average flight 

time equal to or higher than 1.5 flight hours 

per flight cycle. For determining the ‘‘short 

range’’ and ‘‘long range’’ airplanes, the AFT 

is the total accumulated flight hours, counted 

from take-off to touch-down, divided by the 

total accumulated flight cycles at the 

effective date of this AD. 

TABLE 1 TO PARAGRAPH (g) OF THIS

AD—MODEL A310–200 SERIES

AIRPLANES

Compliance time 

(whichever occurs later, A or B) 

A Before exceeding 28,800 flight cycles 

(FC) or 57,600 flight hours (FH), whichever 

occurs first since first flight of the airplane. 

B Within 960 FC, or 1,920 FH, or 12 

months, whichever occurs first after the effective date of this AD. 

TABLE 2 TO PARAGRAPH (g) OF THIS

AD—MODEL A310–300 ‘‘SHORTRANGE’’ AIRPLANES

Compliance time 

(whichever occurs later, A or B) 

A Before exceeding 27,700 FC or 77,700 

FH, whichever occurs first since first flight 

of the airplane. 

B Within 920 FC, or 2,580 FH, or 12 

months, whichever occurs first after the effective date of this AD. 

TABLE 3 TO PARAGRAPH (g) OF THIS

AD—MODEL A310–300 ‘‘LONGRANGE’’ AIRPLANES

Compliance time 

(whichever occurs later, A or B) 

A Before exceeding 20,500 FC or 102,500 

FH, whichever occurs first since first flight 

of the airplane. 

B Within 680 FC, or 3,420 FH, or 12 

months, whichever occurs first after the effective date of this AD. 

(h) Exception to Service Information 

Specifications 

Where Airbus Service Bulletin A310–57– 

2104, dated December 15, 2015, specifies to 

contact Airbus for appropriate action, and 

specifies that action as ‘‘RC’’ (Required for 

Compliance): Before further flight, 

accomplish corrective actions in accordance 

with the procedures specified in paragraph 

(i)(2) of this AD. 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Section, Transport Standards 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 International Section, send it 

to the attention of the person identified in 

paragraph (j)(2) of this AD. Information may 

be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov. 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. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, International Section, 

Transport Standards Branch, FAA; or the 

European Aviation Safety Agency (EASA); or 

Airbus’s EASA Design Organization 

Approval (DOA). If approved by the DOA, 

the approval must include the DOAauthorized signature. 

(3) Required for Compliance (RC): Except 

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

any service information contains procedures 

or tests that are identified as RC, those 

procedures and tests must be done to comply 

with this AD; any procedures or tests that are 

not identified as RC are recommended. Those 

procedures and tests that are not identified 

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 procedures and tests identified as RC can 

be done and the airplane can be put back in 

an airworthy condition. Any substitutions or 

changes to procedures or tests identified as 

RC require approval of an AMOC. 


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40686 Federal Register / Vol. 82, No. 165 / Monday, August 28, 2017 / Rules and Regulations 

(j) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2016–0170, dated 

August 19, 2016, for related information. 

This MCAI may be found in the AD docket 

on the Internet at http://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2017–0472. 

(2) For more information about this AD, 

contact Dan Rodina, Aerospace Engineer, 

International Section, Transport Standards 

Branch, FAA, 1601 Lind Avenue SW., 

Renton, WA 98057–3356; telephone 425– 

227–2125; fax 425–227–1149. 

(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 this AD specifies otherwise. 

(i) Airbus Service Bulletin A310–57–2104, 

dated December 15, 2015. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAW, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 61 

93 44 51; email account.airworth-eas@

airbus.com; Internet http://www.airbus.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 August 

9, 2017. 

Dionne Palermo, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2017–17537 Filed 8–25–17; 8:45am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–0512; Product 

Identifier 2017–NM–031–AD; Amendment 

39–19005; AD 2017–17–15] 

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–600–2E25 

(Regional Jet Series 1000) airplanes. 

This AD was prompted by reports of 

failures of the landing gear alternateextension system. This AD requires 

replacement of certain nose landing gear 

and main landing gear electromechanical actuators. We are issuing 

this AD to address the unsafe condition 

on these products. 

DATES: This AD is effective October 2, 

2017. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of October 2, 2017. 

ADDRESSES: For service information 

identified in this final rule, contact 

Bombardier, Inc., 400 Coˆte-Vertu Road 

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

Widebody Customer Response Center 

North America toll-free telephone 1– 

866–538–1247 or direct-dial telephone: 

1–514–855–2999; fax: 514–855–7401; 

email: ac.yul@aero.bombardier.com; 

Internet: http://www.bombardier.com. 

You may view this referenced 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–2017– 

0512. 

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–2017– 

0512; 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: 

Cesar Gomez, Aerospace Engineer, 

Airframe and Mechanical Systems 

Section, FAA, New York ACO Branch, 

1600 Stewart Avenue, Suite 410, 

Westbury, NY 11590; telephone: 516– 

228–7318; 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–600–2E25 (Regional Jet Series 1000) 

airplanes. The NPRM published in the 

Federal Register on June 2, 2017 (82 FR 

25545) (‘‘the NPRM’’). The NPRM was 

prompted by reports of failures of the 

landing gear alternate-extension system 

(AES). The NPRM proposed to require 

replacement of certain nose landing gear 

and main landing gear electromechanical actuators. We are issuing 

this AD to prevent failure of the landing 

gear AES and consequent landing with 

some or all of the landing gear not 

extended. 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian AD 

CF–2017–08, dated February 22, 2017 

(referred to after this as the Mandatory 

Continuing Airworthiness Information, 

or ‘‘the MCAI’’), to correct an unsafe 

condition for certain Bombardier, Inc., 

Model CL–600–2E25 (Regional Jet Series 

1000) airplanes. The MCAI states: 

Malfunctions of the landing gear AlternateExtension System (AES) have been 

experienced. Failure of the landing gear AES 

could prevent the landing gear from 

extending in the case of a failure of the 

primary landing gear extension system. 

This [Canadian] AD is issued to mandate 

the replacement of the [nose landing gear] 

NLG and [main landing gear] MLG [electromechanical actuators] EMA [part numbers] P/ 

Ns BA698–85006–1 and BA698–85007–1. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2017– 

0512. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting this AD 

as proposed except for 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. 


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