Federal Register / Vol. 83, No. 158 / Wednesday, August 15, 2018 / Rules and Regulations 40445 

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): 

2018–17–03 The Boeing Company: 

Amendment 39–19357; Docket No. 

FAA–2017–1022; Product Identifier 

2017–NM–098–AD. 

(a) Effective Date 

This AD is effective September 19, 2018. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 787–8 and 787–9 airplanes, 

certificated in any category, as identified in 

Boeing Alert Service Bulletin B787–81205– 

SB300019–00, Issue 002, dated April 20, 

2018. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 30, Ice/Rain protection system 

wiring. 

(e) Unsafe Condition 

This AD was prompted by reports of 

failures of the Cabin Air Compressor (CAC) 

inlet ice protection system (CIPS) inlet lip 

heater assemblies due to chafing of the CIPS 

inlet lip heater wire harness against adjacent 

structures. We are issuing this AD to address 

any damage to the CIPS inlet lip heater wire 

bundle, which could cause an electrical short 

and potential loss of functions essential for 

safe flight of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

Within 36 months after the effective date 

of this AD, do all applicable actions 

identified as ‘‘RC’’ (required for compliance) 

in, and in accordance with, the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin B787–81205–SB300019–00, 

Issue 002, dated April 20, 2018. 

(h) Credit for Previous Actions 

(1) This paragraph provides credit for the 

actions specified in paragraph (g) of this AD, 

if those actions were performed before the 

effective date of this AD using Boeing Alert 

Service Bulletin B787–81205–SB300019–00, 

Issue 001, dated March 22, 2017. 

(2) This paragraph provides credit for the 

actions specified in paragraph (g) of this AD, 

if those actions were performed before the 

effective date of this AD using Boeing Alert 

Service Bulletin B787–81205–SB300019–00, 

Issue 001, dated March 22, 2017, in 

conjunction with Boeing Information Notice 

B787–A–30–00–0019–02A–931E–D, Issue 

001, dated December 15, 2017. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle 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 (j) of this 

AD. Information may be emailed to: 9-ANMSeattle-ACO-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, Seattle 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 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 Joe Salemeh, Aerospace Engineer, 

Systems and Equipment Section, FAA, 

Seattle ACO Branch, 2200 South 216th 

Street, Des Moines, WA 98198; phone and 

fax: 206–231–3536; email: joe.salameh@

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 B787– 

81205–SB300019–00, Issue 002, dated April 

20, 2018. 

(ii) Reserved. 

(3) For Boeing 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, 

2200 South 216th St., Des Moines, WA. For 

information on the availability of this 

material at the FAA, call 206–231–3195. 

(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/ibr-locations.html. 

Issued in Des Moines, Washington, on 

August 5, 2018. 

Michael Kaszycki, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2018–17481 Filed 8–14–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0028; Product 

Identifier 2017–NM–143–AD; Amendment 

39–19356; AD 2018–17–02] 

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–600–1A11 

(600), CL–600–2A12 (601), and CL–600– 

2B16 (601–3A, 601–3R, and 604 

Variants) airplanes. This AD was 

prompted by a determination that the 

safe life limits of the horizontal 

stabilizer trim actuator (HSTA) 

attachment pins and trunnions were not 

listed in certain airworthiness 

limitations (AWLs) and that the HSTA 

attachment pins and trunnions were not 

serialized. This AD requires revision of 

the maintenance or inspection program, 

as applicable, to include the latest 

revision of the AWLs, serialization of 

the HSTA attachment pins and 

trunnions, and repair or replacement of 

damaged HSTA attachment pins and 


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40446 Federal Register / Vol. 83, No. 158 / Wednesday, August 15, 2018 / Rules and Regulations 

trunnions. We are issuing this AD to 

address the unsafe condition on these 

products. 

DATES: This AD is effective September 

19, 2018. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of September 19, 2018. 

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, 2200 South 216th St., 

Des Moines, WA. For information on the 

availability of this material at the FAA, 

call 206–231–3195. It is also available 

on the internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2018– 

0028. 

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–2018– 

0028; 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: Aziz 

Ahmed, Aerospace Engineer, Airframe 

and Mechanical Systems Section, FAA, 

New York ACO Branch, 1600 Stewart 

Avenue, Suite 410, Westbury, NY 

11590; telephone 516–228–7239; fax 

516–794–5531; email 9-avs-nyaco-cos@

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 certain Bombardier, Inc., Model 

CL–600–1A11 (600), CL–600–2A12 

(601), and CL–600–2B16 (601–3A, 601– 

3R, and 604 Variants) airplanes. The 

NPRM published in the Federal 

Register on February 8, 2018 (83 FR 

5587) (‘‘the NPRM’’). The NPRM was 

prompted by a determination that the 

safe life limits of the HSTA attachment 

pins and trunnions were not listed in 

certain AWLs and that the HSTA 

attachment pins and trunnions were not 

serialized. The NPRM proposed to 

require revision of the maintenance or 

inspection program, as applicable, to 

include the latest revision of the AWLs, 

serialization of the HSTA attachment 

pins and trunnions, and repair or 

replacement of damaged HSTA 

attachment pins and trunnions. We are 

issuing this AD to address failure of the 

HSTA attachment pins and trunnions, 

which could lead to a disconnect of the 

horizontal stabilizer and subsequent 

loss of the airplane. 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian AD 

CF–2017–24, dated July 12, 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–600–1A11 (600), CL–600– 

2A12 (601), and CL–600–2B16 (601–3A, 

601–3R, and 604 Variants) airplanes. 

The MCAI states: 

During a review of the Horizontal 

Stabilizer Trim Actuator (HSTA) system, it 

was discovered that the safe life limits of the 

HSTA attachment pins and trunnions were 

not listed in the Airworthiness Limitation 

(AWL) Section of the Instructions for 

Continued Airworthiness. Also, the HSTA 

attachment pins and trunnions were not 

serialized making it impossible to keep 

accurate records of the life of these parts. 

Failure of these pins and trunnions could 

lead to a disconnect of the horizontal 

stabilizer and subsequent loss of the 

aeroplane. 

This [Canadian] AD mandates the 

incorporation of AWL tasks into the 

maintenance schedule and serialization of 

HSTA attachment pins and trunnions. Some 

aircraft require AWL tasks and serialization 

of the attachment pins only, while others 

require AWL tasks and serialization of the 

trunnions and attachment pins [and repair or 

replacement if damaged (including linear 

scratches, pits, spalling, dents, or surface 

texture variations)]. 

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–2018– 

0028. 

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. 

Request To Allow Using Later 

Revisions of the Service Information 

NetJets requested that paragraph (h) of 

the proposed AD be revised to specify 

the latest time limits/maintenance 

checks (TLMC) revisions. NetJets noted 

that some of the TLMC documents 

referenced in the proposed AD have 

been revised. NetJets also requested that 

we revise the proposed AD so that 

operators can use later approved 

revisions of the TLMC documents to 

show compliance without requesting an 

alternative method of compliance 

(AMOC). 

We partially agree with the 

commenter’s request. In this 

circumstance, the specific tasks required 

by this AD have not changed in the 

latest available service information from 

the earlier revisions of the service 

information specified in the NPRM. We 

have therefore revised this AD to refer 

to the latest available service 

information and revised paragraph (k) of 

this AD to provide credit for actions 

done using earlier revisions of certain 

service information. However, we may 

not refer to any document that does not 

yet exist. In general terms, we are 

required by Office of the Federal 

Register (OFR) regulations to either 

publish the service document contents 

as part of the actual AD language; or 

submit the service document to the OFR 

for approval as ‘‘referenced’’ material, in 

which case we may only refer to such 

material in the text of an AD. The AD 

may refer to the service document only 

if the OFR approved it for 

‘‘incorporation by reference.’’ See 1 CFR 

part 51. 

To allow operators to use later 

revisions of the referenced document 

(issued after publication of the AD), 

either we must revise the AD to 

reference specific later revisions, or 

operators must request approval to use 

later revisions as an AMOC with this 

AD under the provisions of paragraph 

(m)(1) of this AD. We cannot reference 

a specific revision not yet in existence 

so the only option is to request an 

AMOC. 

Request To Use a Service Bulletin 

Instead of a TLMC 

Disney Aviation Group requested that 

the proposed AD be revised to use 

actions in a service bulletin instead of 

the TLMC for any required inspections. 

The commenter noted that most 

operators have an electronic 

subscription that automatically gives 

them the newest revision of the TLMC 

documents. The commenter stated that 

since the TLMCs have been updated 

since the draft AD was issued, operators 


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Federal Register / Vol. 83, No. 158 / Wednesday, August 15, 2018 / Rules and Regulations 40447 

will not be able to comply with the AD, 

and will have to request an AMOC. The 

commenter noted that service bulletins 

are not revised as often as TLMC 

documents, and when they are updated 

they are not superseded by future 

revisions. The commenter pointed out 

that other manufacturers issue service 

bulletins with similar requirements and 

the related ADs require those service 

bulletins. 

We disagree with the commenter’s 

request. As noted previously, we have 

revised this AD to refer to the latest 

available TLMC documents. We cannot, 

however, mandate how a given 

manufacturer makes their service 

information available. Since 

Bombardier, Inc. has chosen to provide 

the TLMCs in a separate document, 

rather than a service bulletin, that is 

what operators must use to show 

compliance with this AD. We have 

therefore not changed 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 

Bombardier has issued the following 

service information. 

The following service information 

describes procedures for serializing the 

HSTA attachment pins and trunnions. 

These documents are distinct since they 

apply to different airplane models in 

different configurations. 

• Bombardier Service Bulletin 600– 

0760, Revision 01, dated April 21, 2017. 

• Bombardier Service Bulletin 601– 

0626, Revision 01, dated April 21, 2017. 

• Bombardier Service Bulletin 604– 

27–034, Revision 01, dated April 21, 

2017. 

• Bombardier Service Bulletin 605– 

27–005, Revision 01, dated April 21, 

2017. 

The following service information 

identifies airworthiness limitation tasks 

for revising the life limits for HSTA 

attachment pins and trunnions. These 

documents are distinct since they apply 

to different airplane models in different 

configurations. 

• Section 5–10–10, ‘‘Time Limits 

(Structural),’’ of Section 5–10–00, 

‘‘Airworthiness Limitations,’’ of 

Bombardier Challenger 600 Time 

Limits/Maintenance Checks, Publication 

No. PSP 605, Revision 39, dated January 

8, 2018. 

• Section 5–10–10, ‘‘Time Limits 

(Structural)—Pre SB 601–0280,’’ of 

Section 5–10–00, ‘‘Airworthiness 

Limitations,’’ of Bombardier Challenger 

601 Time Limits/Maintenance Checks, 

Publication No. PSP 601–5, Revision 46, 

dated January 8, 2018. 

• Section 5–10–11, ‘‘Time Limits 

(Structural)—Post SB 601–0280,’’ of 

Section 5–10–00, ‘‘Airworthiness 

Limitations,’’ of Bombardier Challenger 

601 Time Limits/Maintenance Checks, 

Publication No. PSP 601–5, Revision 46, 

dated January 8, 2018. 

• Section 5–10–12, ‘‘Time Limits 

(Structural)—Post SB 601–0360,’’ of 

Section 5–10–00, ‘‘Airworthiness 

Limitations,’’ of Bombardier Challenger 

601 Time Limits/Maintenance Checks, 

Publication No. PSP 601–5, Revision 46, 

dated January 8, 2018. 

• Section 5–10–10, ‘‘Time Limits 

(Structural),’’ of Section 5–10–00, 

‘‘Airworthiness Limitations,’’ of 

Bombardier Challenger 601 Time 

Limits/Maintenance Checks, Publication 

No. PSP 601A–5, Revision 42, dated 

January 8, 2018. 

• Section 5–10–11, ‘‘Time Limits 

(Structural),’’ of Section 5–10–00, 

‘‘Airworthiness Limitations,’’ of 

Bombardier Challenger 601 Time 

Limits/Maintenance Checks, Publication 

No. PSP 601A–5, Revision 42, dated 

January 8, 2018. 

• Section 5–10–12, ‘‘Time Limits 

(Structural),’’ of Section 5–10–00, 

‘‘Airworthiness Limitations,’’ of 

Bombardier Challenger 601 Time 

Limits/Maintenance Checks, Publication 

No. PSP 601A–5, Revision 42, dated 

January 8, 2018. 

The following service information 

describes life limits for certain HSTA 

attachment pins and trunnion supports. 

These documents are distinct since they 

apply to different airplane models in 

different configurations. 

• Section 5–10–10, ‘‘Life Limits 

(Structures),’’ of Bombardier Challenger 

604 CL–604 Time Limits/Maintenance 

Checks, Part 2 Airworthiness 

Limitations, Revision 30, dated 

December 4, 2017. This service 

information describes, among other 

tasks: Task 27–42–01–108, ‘‘Discard of 

the Horizontal-Stabilizer Trim-Actuator 

(HSTA) Trunnion Support; Part No. 

601R92386–1/–3;’’ and Task 27–42–01– 

112, ‘‘Discard of the HorizontalStabilizer Trim-Actuator (HSTA) Upper 

and Lower Attachment Pins; Upper Pin 

Part No. 600–92384–5/–7 or 

601R92310–1/–3 and Lower Pin Part 

No. 600–92383–5/–7 or 601R92309–1/– 

3.’’ 

• Section 5–10–10, ‘‘Life Limits 

(Structures),’’ of Bombardier Challenger 

605 CL–605 Time Limits/Maintenance 

Checks, Part 2 Airworthiness 

Limitations, Revision 18, dated 

December 4, 2017. This service 

information describes, among other 

tasks: Task 27–42–01–108, ‘‘Discard of 

the Horizontal-Stabilizer Trim-Actuator 

(HSTA) Trunnion Support; Part No. 

601R92386–1/–3;’’ and Task 27–42–01– 

112, ‘‘Discard of the HorizontalStabilizer Trim-Actuator (HSTA) Upper 

and Lower Attachment Pins; Upper Pin 

Part No. 600–92384–5/–7 or 

601R92310–1/–3 and Lower Pin Part 

No. 600–92383–5/–7 or 601R92309–1/ 

–3.’’ 

• Section 5–10–10, ‘‘Life Limits 

(Structures),’’ of Bombardier Challenger 

650 CL–650 Time Limits/Maintenance 

Checks, Part 2 Airworthiness 

Limitations, Revision 5, dated December 

4, 2017. This service information 

describes, among other tasks: Task 27– 

42–01–108, ‘‘Discard of the HorizontalStabilizer Trim-Actuator (HSTA) 

Trunnion Support; Part No. 601R92386– 

1/–3;’’ and Task 27–42–01–112, 

‘‘Discard of the Horizontal-Stabilizer 

Trim-Actuator (HSTA) Upper and 

Lower Attachment Pins; Upper Pin Part 

No. 600–92384–5/–7 or 601R92310–1/– 

3 and Lower Pin Part No. 600–92383– 

5/–7 or 601R92309–1/–3.’’ 

The following service information 

describes procedures for identifying 

damage to HSTA attachment pins and 

trunnions, and repair or replacement 

instructions. These documents are 

distinct since they apply to different 

airplane models in different 

configurations. 

• Bombardier Repair Engineering 

Order (REO) 600–27–42–002, ‘‘General 

Repair—HSTA Upper and Lower Pins,’’ 

dated December 15, 2016. 

• Bombardier Repair Engineering 

Order (REO) 604–27–42–011, ‘‘General 

Repair—HSTA Trunnion P/N 

601R92386–1/–3,’’ dated December 15, 

2016. 

• Bombardier Repair Engineering 

Order (REO) 604–27–42–012, ‘‘General 

Repair—HSTA Upper and Lower Pins,’’ 

dated December 15, 2016. 

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. 


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40448 Federal Register / Vol. 83, No. 158 / Wednesday, August 15, 2018 / Rules and Regulations 

Costs of Compliance 

We estimate that this AD affects 137 

airplanes of U.S. registry. We estimate 

the following costs to comply with this 

AD: 

ESTIMATED COSTS FOR REQUIRED ACTIONS

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

operators 

Serialization ............... Up to 20 work-hours × $85 per hour = Up to $1,700 ................... $449 Up to $2,149 .... Up to $294,413. 

We have determined that revising the 

maintenance or inspection program 

takes an average of 90 work-hours per 

operator, although we recognize that 

this number may vary from operator to 

operator. In the past, we have estimated 

that this action takes 1 work-hour per 

airplane. Since operators incorporate 

maintenance or inspection program 

changes for their affected fleet(s), we 

have determined that a per-operator 

estimate is more accurate than a perairplane estimate. Therefore, we 

estimate the total cost per operator to be 

$7,650 (90 work-hours × $85 per workhour). 

We have received no definitive data 

that would enable 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. 

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 

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): 

2018–17–02 Bombardier, Inc.: Amendment 

39–19356; Docket No. FAA–2018–0028; 

Product Identifier 2017–NM–143–AD. 

(a) Effective Date 

This AD is effective September 19, 2018. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the Bombardier, Inc., 

airplanes identified in paragraphs (c)(1) 

through (c)(4) of this AD, certificated in any 

category. 

(1) Model CL–600–1A11 (600) airplanes, 

serial numbers 1002 and 1004 through 1085 

inclusive. 

(2) Model CL–600–2A12 (601) airplanes, 

serial numbers 3001 through 3066 inclusive. 

(3) Model CL–600–2B16 (601–3A and 601– 

3R Variants) airplanes, serial numbers 5001 

through 5194 inclusive. 

(4) Model CL–600–2B16 (604 Variant) 

airplanes, serial numbers 5301 through 5665 

inclusive, 5701 through 5990 inclusive, and 

6050 and subsequent. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 27, Flight controls. 

(e) Reason 

This AD was prompted by a determination 

that the safe life limits of the horizontal 

stabilizer trim actuator (HSTA) attachment 

pins and trunnions were not listed in certain 

airworthiness limitations (AWLs) and that 

the HSTA attachment pins and trunnions 

were not serialized. We are issuing this AD 

to prevent failure of the HSTA attachment 

pins and trunnions, which could lead to a 

disconnect of the horizontal stabilizer and 

subsequent loss of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Maintenance or Inspection Program 

Revision for Model CL–600–1A11 (600), 

Model CL–600–2A12 (601), and Model CL– 

600–2B16 (601–3A and 601–3R Variants) 

Airplanes 

For airplanes identified in paragraphs 

(c)(1), (c)(2), and (c)(3) of this AD: Within 60 

days after the effective date of this AD, revise 

the maintenance or inspection program, as 

applicable, to incorporate the life limit AWL 

tasks identified in table 1 to paragraph (g) of 

this AD, as specified in the applicable service 

information identified in paragraph (g)(1), 

(g)(2), or (g)(3) of this AD. The initial 

compliance time is within 500 flight cycles 

of the effective date of this AD, or at the 

applicable time (in terms of landings) 

specified in the applicable AWL task 

identified in table 1 to paragraph (g) of this 

AD, whichever occurs later. 


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Federal Register / Vol. 83, No. 158 / Wednesday, August 15, 2018 / Rules and Regulations 40449 

(1) For Model CL–600–1A11 (600) 

airplanes, Section 5–10–10, ‘‘Time Limits 

(Structural),’’ of Section 5–10–00, 

‘‘Airworthiness Limitations,’’ of Bombardier 

Challenger 600 Time Limits/Maintenance 

Checks, Publication No. PSP 605, Revision 

39, dated January 8, 2018. 

(2) For Model CL–600–2A12 (601) 

airplanes, the applicable task specified in 

paragraph (g)(2)(i), (g)(2)(ii), or (g)(2)(iii) of 

this AD, as identified in Section 5–10–00, 

‘‘Airworthiness Limitations,’’ of Bombardier 

Challenger 601 Time Limits/Maintenance 

Checks, Publication No. PSP 601–5, Revision 

46, dated January 8, 2018. 

(i) Section 5–10–10, ‘‘Time Limits 

(Structural)—Pre SB 601¥0280.’’ 

(ii) Section 5–10–11, ‘‘Time Limits 

(Structural)—Post SB 601¥0280.’’ 

(iii) Section 5–10–12, ‘‘Time Limits 

(Structural)—Post SB 601¥0360.’’ 

(3) For Model CL–600–2B16 (601–3A and 

601–3R Variants) airplanes, the applicable 

task specified in paragraph (g)(3)(i), (g)(3)(ii), 

or (g)(3)(iii) of this AD, as identified in 

Section 5–10–00, ‘‘Airworthiness 

Limitations,’’ of Bombardier Challenger 601 

Time Limits/Maintenance Checks, 

Publication No. PSP 601A–5, Revision 42, 

dated January 8, 2018. 

(i) Section 5–10–10, ‘‘Time Limits 

(Structural).’’ 

(ii) Section 5–10–11, ‘‘Time Limits 

(Structural).’’ 

(iii) Section 5–10–12, ‘‘Time Limits 

(Structural).’’ 

(h) Maintenance or Inspection Program 

Revision for Model CL–600–2B16 (604 

Variant) Airplanes 

For airplanes identified in paragraph (c)(4) 

of this AD: Within 60 days after the effective 

date of this AD, revise the maintenance or 

inspection program, as applicable, to 

incorporate new life limit AWL Task 27–42– 

01–108, ‘‘Discard of the Horizontal-Stabilizer 

Trim-Actuator (HSTA) Trunnion Support; 

Part No. 601R92386–1/–3,’’ and Task 27–42– 

01–112, ‘‘Discard of the Horizontal-Stabilizer 

Trim-Actuator (HSTA) Upper and Lower 

Attachment Pins; Upper Pin Part No. 600– 

92384–5/–7 or 601R92310–1/–3 and Lower 

Pin Part No. 600–92383–5/–7 or 601R92309– 

1/–3,’’ as specified in the applicable time 

limits maintenance checks (TLMC) manuals 

identified in paragraphs (h)(1), (h)(2), and 

(h)(3) of this AD. The initial compliance time 

is within 500 flight cycles after the effective 

date of this AD, or at the applicable time 

specified in the applicable AWL task, 

whichever occurs later. 

(1) For airplanes having serial numbers 

5301 through 5665 inclusive: Section 5–10– 

10, ‘‘Life Limits (Structures),’’ of Bombardier 

Challenger 604 CL–604 Time Limits/ 

Maintenance Checks, Part 2 Airworthiness 

Limitations, Revision 30, dated December 4, 

2017. 

(2) For airplanes having serial numbers 

5701 through 5990 inclusive: Section 5–10– 

10, ‘‘Life Limits (Structures),’’ of Bombardier 

Challenger 605 CL–605 Time Limits/ 

Maintenance Checks, Part 2 Airworthiness 

Limitations, Revision 18, dated December 4, 

2017. 

(3) For airplanes having serial numbers 

6050 and subsequent: Section 5–10–10, ‘‘Life 

Limits (Structures),’’ of Bombardier 

Challenger 650 CL–650 Time Limits/ 

Maintenance Checks, Part 2 Airworthiness 

Limitations, Revision 5, dated December 4, 

2017. 

(i) Serialization of HSTA Attachment Pins 

and Trunnions 

For airplanes identified in table 2 to 

paragraph (i) of this AD: Within 48 months 

after the effective date of this AD, or prior to 

performing a maintenance task required by 

paragraph (g) or (h) of this AD, as applicable, 

whichever occurs first, do a general visual 

inspection for damage (including linear 

scratches, pits, spalling, dents, or surface 

texture variations), and add serial numbers to 

the HSTA trunnions, lower attachment pin, 

and upper attachment pin, as applicable, in 

accordance with the Accomplishment 

Instructions of the applicable service 

information specified in table 2 to paragraph 

(i) of this AD. If any damage to the HSTA 

trunnions or attachment pins is found, repair 

the damage in accordance with the 

applicable service information specified in 

paragraph (i)(1), (i)(2), or (i)(3) of this AD; or 

using a method approved by the Manager, 

New York ACO Branch, FAA; or Transport 

Canada Civil Aviation (TCCA); or 

Bombardier, Inc.’s TCCA Design Approval 

Organization (DAO). If approved by the DAO, 

the approval must include the DAOauthorized signature. If the damaged HSTA 

trunnion or attachment pin cannot be 

repaired in accordance with the applicable 

service information specified in paragraph 

(i)(1), (i)(2), or (i)(3) of this AD: Before further 

flight, replace the damaged HSTA trunnion 

or attachment pin with a serviceable 

serialized HSTA trunnion or attachment pin, 

in accordance with the applicable service 

information specified in table 2 to paragraph 

(i) of this AD. 

(1) Bombardier Repair Engineering Order 

(REO) 600–27–42–002, ‘‘General Repair— 

HSTA Upper and Lower Pins,’’ dated 

December 15, 2016. 

(2) Bombardier Repair Engineering Order 

(REO) 604–27–42–011, ‘‘General Repair— 

HSTA Trunnion P/N 601R92386–1/–3,’’ 

dated December 15, 2016. 

(3) Bombardier Repair Engineering Order 

(REO) 604–27–42–012, ‘‘General Repair— 

HSTA Upper and Lower Pins,’’ dated 

December 15, 2016. 

BILLING CODE 4910–13–P 


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BILLING CODE 4910–13–C 

(j) No Alternative Actions or Intervals 

After the maintenance or inspection 

program has been revised as required by 

paragraph (g) or (h) 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 (m)(1) of 

this AD. 

(k) Credit for Previous Actions 

(1) This paragraph provides credit for 

actions required by paragraph (g) of this AD, 

if those actions were performed before the 

effective date of this AD using the service 

information specified in paragraph (k)(1)(i), 

(k)(1)(ii), or (k)(1)(iii) of this AD, as 

applicable. 

(i) Section 5–10–10, ‘‘Time Limits 

(Structural),’’ of Section 5–10–00, 

‘‘Airworthiness Limitations,’’ of Bombardier 

Challenger 600 Time Limits/Maintenance 

Checks, Publication No. PSP 605, Revision 

38, dated March 28, 2017. 

(ii) Section 5–10–10, ‘‘Time Limits 

(Structural)—Pre SB 601–0280,’’ of Section 

5–10–00, ‘‘Airworthiness Limitations,’’ of 

Bombardier Challenger 601 Time Limits/ 

Maintenance Checks, Publication No. PSP 

601–5, Revision 45, dated March 28, 2017. 

(iii) Section 5–10–11, ‘‘Time Limits 

(Structural)—Post SB 601–0280,’’ of Section 

5–10–00, ‘‘Airworthiness Limitations,’’ of 

Bombardier Challenger 601 Time Limits/ 

Maintenance Checks, Publication No. PSP 

601–5, Revision 45, dated March 28, 2017. 

(iv) Section 5–10–12, ‘‘Time Limits 

(Structural)—Post SB 601–0360,’’ of Section 

5–10–00, ‘‘Airworthiness Limitations,’’ of 

Bombardier Challenger 601 Time Limits/ 

Maintenance Checks, Publication No. PSP 

601–5, Revision 45, dated March 28, 2017. 

(v) Section 5–10–10, ‘‘Time Limits 

(Structural),’’ of Section 5–10–00, 

‘‘Airworthiness Limitations,’’ of Bombardier 

Challenger 601 Time Limits/Maintenance 

Checks, Publication No. PSP 601A–5, 

Revision 41, dated March 28, 2017. 

(vi) Section 5–10–11, ‘‘Time Limits 

(Structural),’’ of Section 5–10–00, 

‘‘Airworthiness Limitations,’’ of Bombardier 

Challenger 601 Time Limits/Maintenance 

Checks, Publication No. PSP 601A–5, 

Revision 41, dated March 28, 2017. 

(vii) Section 5–10–12, ‘‘Time Limits 

(Structural),’’ of Section 5–10–00, 

‘‘Airworthiness Limitations,’’ of Bombardier 

Challenger 601 Time Limits/Maintenance 

Checks, Publication No. PSP 601A–5, 

Revision 41, dated March 28, 2017. 

(2) 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 the service 

information specified in paragraph (k)(2)(i), 

(k)(2)(ii), or (k)(2)(iii) of this AD, as 

applicable. 

(i) Section 5–10–10, ‘‘Life Limits 

(Structures),’’ of Bombardier Challenger 604 

CL–604 Time Limits/Maintenance Checks, 

Part 2 Airworthiness Limitations, Revision 

29, dated June 16, 2017. 

(ii) Section 5–10–10, ‘‘Life Limits 

(Structures),’’ of Bombardier Challenger 605 

CL–605 Time Limits/Maintenance Checks, 

Part 2 Airworthiness Limitations, Revision 

17, dated June 16, 2017. 

(iii) Section 5–10–10, ‘‘Life Limits 

(Structures),’’ of Bombardier Challenger 650 

CL–650 Time Limits/Maintenance Checks, 

Part 2 Airworthiness Limitations, Revision 4, 

dated June 16, 2017. 

(3) This paragraph provides credit for 

actions required by paragraph (i) of this AD, 

if those actions were performed before the 

effective date of this AD using the service 

information specified in paragraph (k)(3)(i), 

(k)(3)(ii), (k)(3)(iii), or (k)(3)(iv) of this AD, as 

applicable. 

(i) Bombardier Service Bulletin 600–0760, 

dated February 25, 2013. 

(ii) Bombardier Service Bulletin 601–0626, 

dated February 25, 2013. 

(iii) Bombardier Service Bulletin 604–27– 

034, dated February 25, 2013. 

(iv) Bombardier Service Bulletin 605–27– 

005, dated February 25, 2013. 


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Federal Register / Vol. 83, No. 158 / Wednesday, August 15, 2018 / Rules and Regulations 40451 

(l) Parts Installation Limitations 

(1) As of the effective date of this AD, no 

person may install, on any airplane, an HSTA 

attachment pin, unless the pin has a serial 

number. 

(2) As of the effective date of this AD, no 

person may install, on any Bombardier, Inc., 

Model CL–600–2B16 (604 Variant) airplane 

with serial number 5301 and subsequent, an 

HSTA trunnion, unless the HSTA trunnion 

has a serial number. 

(m) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York 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 ATTN: Program Manager, 

Continuing Operational Safety, FAA, New 

York ACO Branch, 1600 Stewart Avenue, 

Suite 410, Westbury, NY 11590; telephone 

516–228–7300; fax 516–794–5531. 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, New York ACO Branch, 

FAA; or TCCA; or Bombardier, Inc.’s TCCA 

DAO. If approved by the DAO, the approval 

must include the DAO-authorized signature. 

(n) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

AD CF–2017–24, dated July 12, 2017, 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–2018–0028. 

(2) For more information about this AD, 

contact Aziz Ahmed, Aerospace Engineer, 

Airframe and Mechanical Systems Section, 

FAA, New York ACO Branch, 1600 Stewart 

Avenue, Suite 410, Westbury, NY 11590; 

telephone 516–228–7239; fax 516–794–5531; 

email 9-avs-nyaco-cos@faa.gov. 

(3) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

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

(o) 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) Bombardier Repair Engineering Order 

(REO) 600–27–42–002, ‘‘General Repair— 

HSTA Upper and Lower Pins,’’ dated 

December 15, 2016. 

(ii) Bombardier Repair Engineering Order 

(REO) 604–27–42–011, ‘‘General Repair— 

HSTA Trunnion P/N 601R92386–1/–3,’’ 

dated December 15, 2016. 

(iii) Bombardier Repair Engineering Order 

(REO) 604–27–42–012, ‘‘General Repair— 

HSTA Upper and Lower Pins,’’ dated 

December 15, 2016. 

(iv) Bombardier Service Bulletin 600–0760, 

Revision 01, dated April 21, 2017. 

(v) Bombardier Service Bulletin 601–0626, 

Revision 01, dated April 21, 2017. 

(vi) Bombardier Service Bulletin 604–27– 

034, Revision 01, dated April 21, 2017. 

(vii) Bombardier Service Bulletin 605–27– 

005, Revision 01, dated April 21, 2017. 

(viii) Section 5–10–10, ‘‘Time Limits 

(Structural),’’ of Section 5–10–00, 

‘‘Airworthiness Limitations,’’ of Bombardier 

Challenger 600 Time Limits/Maintenance 

Checks, Publication No. PSP 605, Revision 

39, dated January 8, 2018. 

(ix) Section 5–10–00, ‘‘Airworthiness 

Limitations,’’ of Bombardier Challenger 601 

Time Limits/Maintenance Checks, 

Publication No. PSP 601–5, Revision 46, 

dated January 8, 2018. 

(A) Section 5–10–10, ‘‘Time Limits 

(Structural)—Pre SB 601–0280.’’ 

(B) Section 5–10–11, ‘‘Time Limits 

(Structural)—Post SB 601–0280.’’ 

(C) Section 5–10–12, ‘‘Time Limits 

(Structural)—Post SB 601–0360.’’ 

(x) Section 5–10–00, ‘‘Airworthiness 

Limitations,’’ of Bombardier Challenger 601 

Time Limits/Maintenance Checks, 

Publication No. PSP 601A–5, Revision 42, 

dated January 8, 2018. 

(A) Section 5–10–10, ‘‘Time Limits 

(Structural).’’ 

(B) Section 5–10–11, ‘‘Time Limits 

(Structural).’’ 

(C) Section 5–10–12, ‘‘Time Limits 

(Structural).’’ 

(xi) Section 5–10–10, ‘‘Life Limits 

(Structures),’’ of Bombardier Challenger 604 

CL–604 Time Limits/Maintenance Checks, 

Part 2 Airworthiness Limitations, Revision 

30, dated December 4, 2017. 

(xii) Section 5–10–10, ‘‘Life Limits 

(Structures),’’ of Bombardier Challenger 605 

CL–605 Time Limits/Maintenance Checks, 

Part 2 Airworthiness Limitations, Revision 

18, dated December 4, 2017. 

(xiii) Section 5–10–10, ‘‘Life Limits 

(Structures),’’ of Bombardier Challenger 650 

CL–650 Time Limits/Maintenance Checks, 

Part 2 Airworthiness Limitations, Revision 5, 

dated December 4, 2017. 

(3) For service information identified in 

this AD, contact Bombardier, Inc., 400 CoˆteVertu 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. 

(4) You may view this service information 

at the FAA, Transport Standards Branch, 

2200 South 216th St., Des Moines, WA. For 

information on the availability of this 

material at the FAA, call 206–231–3195. 

(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 Des Moines, Washington, on 

August 5, 2018. 

Michael Kaszycki, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2018–17483 Filed 8–14–18; 8:45 am] 

BILLING CODE 4910–13–P 

SOCIAL SECURITY ADMINISTRATION 

20 CFR Parts 404 and 416 

[Docket No. SSA–2018–0033] 

RIN 0960–AI23 

Making Permanent the Attorney 

Advisor Program 

AGENCY: Social Security Administration. 

ACTION: Final rule. 

SUMMARY: We are making permanent the 

attorney advisor program, which has 

proved to be an integral tool in 

providing timely decisions to the public 

while maximizing the use of our 

administrative law judges (ALJs). The 

attorney advisor initiative permits some 

attorney advisors to develop claims, 

including holding prehearing 

conferences, and, in cases in which the 

documentary record clearly establishes 

that a fully favorable decision is 

warranted, issue fully favorable 

decisions before a hearing is conducted. 

We expect that by making the attorney 

advisor program permanent, we will be 

able to continue to reduce the number 

of pending claims at the hearing level of 

our administrative review process and 

provide more timely service to 

claimants. 

DATES: This final rule is effective August 

15, 2018. 

FOR FURTHER INFORMATION CONTACT: 

Susan Swansiger, Office of Hearings 

Operations, Social Security 

Administration, 5107 Leesburg Pike, 

Falls Church, VA 22041, (703) 605– 

8500. For information on eligibility or 

filing for benefits, call our national tollfree number, 800–772–1213 or TTY 

800–325–0778, or visit our internet site, 

Social Security Online, at http://

www.socialsecurity.gov. 

SUPPLEMENTARY INFORMATION: 

Background of the Attorney Advisor 

Program 

Under the attorney advisor program, 

certain attorney advisors may develop 

claims and, in appropriate cases, issue 


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