This section of the FEDERAL REGISTER

contains notices to the public of the proposed

issuance of rules and regulations. The

purpose of these notices is to give interested

persons an opportunity to participate in the

rule making prior to the adoption of the final

rules.

Proposed Rules Federal Register

48668 

Vol. 82, No. 201 

Thursday, October 19, 2017 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–0907; Product 

Identifier 2017–NM–069–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc., Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Bombardier, Inc., Model CL–600–1A11 

(CL–600), CL–600–2A12 (CL–601 

Variant), and CL–600–2B16 (CL–601– 

3A, CL–601–3R, and CL–604 Variants) 

airplanes. This proposed AD was 

prompted by reports of fractured rudder 

pedal tubes on the pilot-side rudder bar 

assembly. This proposed AD would 

require repetitive inspections of the 

rudder pedal tubes for cracking and 

corrective actions if necessary. 

Replacement of both pilot-side rudder 

bar assemblies is terminating action for 

the inspections. We are proposing this 

AD to address the unsafe condition on 

these products. 

DATES: We must receive comments on 

this proposed AD by December 4, 2017. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this NPRM, 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 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. 

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– 

0907; 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 NPRM, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (telephone 

800–647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

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 516–228–7329; fax 

516–794–5531. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2017–0907; Product Identifier 

2017–NM–069–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this NPRM. We will consider 

all comments received by the closing 

date and may amend this NPRM based 

on those comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this NPRM. 

Discussion 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2017–09, 

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– 

600–1A11 (CL–600), CL–600–2A12 (CL– 

601 Variant), and CL–600–2B16 (CL– 

601–3A, CL–601–3R, and CL–604 

Variants) airplanes. The MCAI states: 

There have been two in-service reports of 

fractured rudder pedal tubes installed on the 

pilot-side rudder bar assembly on CL–600– 

2B19 aeroplanes. Laboratory examination of 

the fractured rudder pedal tubes found that 

in both cases, the fatigue cracks initiated at 

the aft taper pin holes where the connecting 

rod fitting is attached. Fatigue testing of the 

rudder pedal tubes confirmed that the fatigue 

cracking is due to loads induced during 

parking brake application. Therefore, only 

the rudder pedal tubes on the pilot’s side are 

vulnerable to fatigue cracking as the parking 

brake is primarily applied by the pilot. 

Loss of pilot rudder pedal input during 

flight would result in reduced yaw 

controllability of the aeroplane. Loss of pilot 

rudder pedal input during takeoff or landing 

may lead to a runway excursion. 

This [Canadian] AD mandates initial and 

repetitive [detailed visual or eddy current] 

inspections [for cracking] of both pilot-side 

rudder pedal tubes, part number (P/N) 600– 

90204–3 until the terminating action in Part 

III of this [Canadian] AD is accomplished 

[i.e., replacement of both pilot-side rudder 

bar assemblies]. 

Corrective actions include 

replacement of both pilot-side rudder 

bar assemblies and 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– 

0907. 

Related Service Information Under 1 

CFR Part 51 

Bombardier, Inc., has issued the 

following service information. The 

service information describes 

procedures for repetitive inspections of 

the rudder pedal tubes for cracking, 

replacement of both pilot-side rudder 

bar assemblies, and repair. These 

documents are distinct since they apply 

to different airplane models. 


rmajette on DSKBCKNHB2PROD with PROPOSALS
Federal Register / Vol. 82, No. 201 / Thursday, October 19, 2017 / Proposed Rules 48669 

• Service Bulletin 600–0770, Revision 

01, including Appendix A, dated March 

31, 2016. 

• Service Bulletin 601–0643, Revision 

01, including Appendix A, dated March 

31, 2016. 

• Service Bulletin 604–27–037, dated 

March 31, 2016, including Appendix A, 

Revision 01, dated March 31, 2016. 

• Service Bulletin 605–27–002, dated 

June 30, 2016, including Appendix A, 

Revision 01, dated March 31, 2016. 

• Service Bulletin 605–27–008, dated 

March 31, 2016, including Appendix A, 

Revision 01, dated March 31, 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. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of these same 

type designs. 

Costs of Compliance 

We estimate that this proposed AD 

affects 141 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 

ESTIMATED COSTS

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

Inspections .......... 10 work-hours × $85 per hour = $850 per inspection cycle.$0 $850 per inspection cycle $119,850 per inspection 

cycle. 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Replacement ....... 2 work-hours × $85 per hour = $170 ........................................................ $8,564 $8,734 $1,231,494 

We have received no definitive data 

that would enable us to provide cost 

estimates for any on-condition repairs 

specified in this proposed AD. We have 

no way of determining the number of 

aircraft that might need this repair. 

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 proposed 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 proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would 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 this proposed regulation: 

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. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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): 

Bombardier, Inc.: Docket No. FAA–2017– 

0907; Product Identifier 2017–NM–069– 

AD. 

(a) Comments Due Date 

We must receive comments by December 4, 

2017. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the Bombardier, Inc., 

airplanes identified in paragraphs (c)(1) 

through (c)(3) of this AD, certificated in any 

category. 

(1) Model CL–600–1A11 (CL–600) 

airplanes, serial numbers (S/Ns) 1004 

through 1085 inclusive. 

(2) Model CL–600–2A12 (CL–601 Variant) 

airplanes, S/Ns 3001 through 3066 inclusive. 

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

601–3R, and CL–604 Variants) airplanes, S/ 


rmajette on DSKBCKNHB2PROD with PROPOSALS
48670 Federal Register / Vol. 82, No. 201 / Thursday, October 19, 2017 / Proposed Rules 

Ns 5001 through 5194 inclusive, S/Ns 5301 

through 5665 inclusive, S/Ns 5701 through 

5988 inclusive, and S/Ns 6050 through 6099 

inclusive. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 27, Flight Controls. 

(e) Reason 

This AD was prompted by reports of 

fractured rudder pedal tubes on the pilot-side 

rudder bar assembly. We are issuing this AD 

to detect and correct cracking of the pilotside rudder pedal tubes. Loss of pilot rudder 

pedal input during flight could result in 

reduced yaw controllability of the airplane. 

Loss of pilot rudder pedal input during 

takeoff or landing could lead to a runway 

excursion. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Inspections and Part Marking 

At the applicable time specified in figure 

1 to paragraph (g) of this AD, do a detailed 

or eddy current inspection of both pilot-side 

rudder pedal tubes for cracking, in 

accordance with Part A of the 

Accomplishment Instructions of the 

applicable service information identified in 

paragraphs (g)(1) through (g)(6) of this AD. If 

no cracking is found, before further flight, 

mark the part in accordance with Part A of 

the Accomplishment Instructions of the 

applicable service information identified in 

paragraphs (g)(1) through (g)(6) of this AD. 

Repeat the detailed or eddy current 

inspection thereafter at intervals not to 

exceed 600 flight cycles if a detailed 

inspection was performed, or 1,000 flight 

cycles if an eddy current inspection was 

performed. Repeat the inspection until the 

terminating action specified in paragraph (i) 

of this AD is accomplished. 

(1) For Model CL–600–1A11 (CL–600) 

airplanes, S/Ns 1004 through 1085 inclusive: 

Bombardier, Inc., Service Bulletin 600–0770, 

Revision 01, including Appendix A, dated 

March 31, 2016. 

(2) For Model CL–600–2A12 (CL–601 

Variant) airplanes, S/Ns 3001 through 3066 

inclusive: Bombardier, Inc., Service Bulletin 

601–0643, Revision 01, including Appendix 

A, dated March 31, 2016. 

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

601–3R, and CL–604 Variants) airplanes, S/ 

Ns 5001 through 5194 inclusive: Bombardier, 

Inc., Service Bulletin 601–0643, Revision 01, 

including Appendix A, dated March 31, 

2016. 

(4) Model CL–600–2B16 (CL–601–3A, CL– 

601–3R, and CL–604 Variants) airplanes, S/ 

Ns 5301 through 5665 inclusive: Bombardier, 

Inc., Service Bulletin 604–27–037, dated 

March 31, 2016, including Appendix A, 

Revision 01, dated March 31, 2016. 

(5) Model CL–600–2B16 (CL–601–3A, CL– 

601–3R, and CL–604 Variants) airplanes, S/ 

Ns 5701 through 5988 inclusive: Bombardier, 

Inc., Service Bulletin 605–27–008, dated 

March 31, 2016, including Appendix A, 

Revision 01, dated March 31, 2016. 

(6) Model CL–600–2B16 (CL–601–3A, CL– 

601–3R, and CL–604 Variants) airplanes, S/ 

Ns 6050 through 6099 inclusive: Bombardier, 

Inc., Service Bulletin 605–27–002, dated June 

30, 2016, including Appendix A, Revision 

01, dated March 31, 2016. 

FIGURE 1 TO PARAGRAPH (g) OF THIS AD—COMPLIANCE TIMES

Airplanes Compliance time 

Airplanes with fewer than 8,250 total flight cycles as of the effective 

date of this AD.

Prior to the accumulation of 9,000 total flight cycles. 

Airplanes with 8,250 total flight cycles or more but fewer than 16,625 

total flight cycles as of the effective date of this AD.

Within 24 months or 750 flight cycles, whichever occurs first, after the 

effective date of this AD. 

Airplanes with 16,625 total flight cycles or more as of the effective date 

of this AD.

Within 12 months or 375 flight cycles, whichever occurs first, after the 

effective date of this AD. 

(h) Corrective Actions 

(1) If any cracking is found around the aft 

tapered holes during any inspection required 

by paragraph (g) of this AD, before further 

flight, replace both pilot-side rudder bar 

assemblies, in accordance with Part B of the 

Accomplishment Instructions of the 

applicable service information identified in 

paragraphs (g)(1) through (g)(6) of this AD. 

(2) If any other damage (e.g., corrosion) is 

found, during any inspection required by 

paragraph (g) of this AD, before further flight, 

repair 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). 

(i) Optional Terminating Action 

Replacement of both pilot-side rudder bar 

assemblies in accordance with Part B of the 

Accomplishment Instructions of the 

applicable service information identified in 

paragraphs (g)(1) through (g)(6) of this AD 

terminates the inspections required by 

paragraph (g) of this AD. 

(j) Replacement—No Terminating Action 

Replacement of both pilot-side rudder bar 

assemblies using Part B of the 

Accomplishment Instructions of Bombardier 

Service Bulletin 600–0770, dated August 31, 

2015; or Bombardier Service Bulletin 601– 

0643, dated August 31, 2015; is not 

terminating action for the inspections 

required by paragraph (g) of this AD. 

(k) 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. 

(l) Special Flight Permits 

Special flight permits, as described in 

Section 21.197 and Section 21.199 of the 

Federal Aviation Regulations (14 CFR 21.197 

and 21.199), are not allowed if any cracking 

is found during any inspection required by 

paragraph (g) of this AD. 

(m) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2017–09, dated 

February 22, 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–2017–0907. 

(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 516–228–7329; fax 516–794–5531. 

(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. You may view this 

service information at the FAA, Transport 

Standards Branch, 1601 Lind Avenue SW., 


rmajette on DSKBCKNHB2PROD with PROPOSALS
Federal Register / Vol. 82, No. 201 / Thursday, October 19, 2017 / Proposed Rules 48671 

Renton, WA. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

Issued in Renton, Washington, on October 

11, 2017. 

Jeffrey E. Duven, 

Director, System Oversight Division, Aircraft 

Certification Service. 

[FR Doc. 2017–22557 Filed 10–18–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–9435; Product 

Identifier 2016–NM–108–AD] 

RIN 2120–AA64 

Airworthiness Directives; Fokker 

Services B.V. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Supplemental notice of 

proposed rulemaking (SNPRM); 

reopening of comment period. 

SUMMARY: We are revising an earlier 

proposal to supersede Airworthiness 

Directive (AD) 2012–22–15, which 

applies to all Fokker Services B.V. 

Model F28 Mark 0070 and Mark 0100 

airplanes. This action revises the notice 

of proposed rulemaking (NPRM) by 

proposing to require incorporating new 

airworthiness limitations into the 

maintenance or inspection program, as 

applicable. We are proposing this AD to 

address the unsafe condition on these 

products. Since these actions would 

impose an additional burden over those 

in the NPRM, we are reopening the 

comment period to allow the public the 

chance to comment on these proposed 

changes. 

DATES: The comment period for the 

NPRM published in the Federal 

Register on December 16, 2016 (81 FR 

91068), is reopened. 

We must receive comments on this 

SNPRM by December 4, 2017. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC, between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. 

For service information identified in 

this SNPRM, contact Fokker Services 

B.V., Technical Services Dept., P.O. Box 

1357, 2130 EL Hoofddorp, the 

Netherlands; telephone +31 (0)88–6280– 

350; fax +31 (0)88–6280–111; email 

technicalservices@fokker.com; Internet 

http://www.myfokkerfleet.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. 

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– 

9435; 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 SNPRM, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Office (telephone: 800–647– 

5527) is in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: Tom 

Rodriguez, Aerospace Engineer, 

International Section, Transport 

Standards Branch, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1137; fax 425–227– 

1149. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2016–9435; Product Identifier 2016– 

NM–108–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this SNPRM. We will 

consider all comments received by the 

closing date and may amend this 

SNPRM based on those comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this SNPRM. 

Discussion 

We issued AD 2012–22–15, 

Amendment 39–17252 (77 FR 68063, 

November 15, 2012) (‘‘AD 2012–22– 

15’’). AD 2012–22–15 requires actions 

intended to address an unsafe condition 

on all Fokker Services B.V. Model F28 

Mark 0070 and Mark 0100 airplanes. 

We issued an NPRM to amend 14 CFR 

part 39 by adding an AD that would 

supersede AD 2012–22–15. The NPRM 

published in the Federal Register on 

December 16, 2016 (81 FR 91068). The 

NPRM was prompted by new and more 

restrictive airworthiness limitations. 

The NPRM proposed to revise the 

maintenance or inspection program, as 

applicable, to incorporate the new and 

more restrictive airworthiness 

limitations. 

Actions Since the NPRM Was Issued 

Since we issued the NPRM, additional 

airworthiness limitations have been 

issued and we have determined it is 

necessary to require revising the 

maintenance or inspection program, as 

applicable, to incorporate the new 

airworthiness limitations. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD 2017–0095, 

dated May 30, 2017 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for all Fokker Services B.V. Model F28 

Mark 0070 and Mark 0100 airplanes. 

The MCAI states: 

Fokker Services Engineering Report SE– 

623 contains the Airworthiness Limitation 

Items (ALIs) and Safe Life Items (SLIs). This 

report is Part 2 of the Airworthiness 

Limitations Section (ALS Part 2) of the 

Instructions for Continued Airworthiness, 

referred to in Section 06, Appendix 1, of the 

Fokker 70/100 Maintenance Review Board 

document. 

The complete ALS consists of: 

Part 1—Report SE–473, Certification 

Maintenance Requirements (CMRs)—ref. 

EASA AD 2015–0027 [which corresponds to 

FAA AD 2016–11–22, Amendment 39–18549 

(81 FR 36438, June 7, 2016)], 

Part 2—Report SE–623, ALIs and SLIs—ref. 

EASA AD 2016–0125 [which corresponds to 

certain requirements in FAA AD 2012–22– 

15], and 

Part 3—Report SE–672, Fuel ALIs and 

CDCCLs—ref. EASA AD 2015–0032 [which 

corresponds to FAA AD 2016–11–15, 

Amendment 39–18542 (81 FR 36447, June 7, 

2016)]. 

The instructions contained in those reports 

have been identified as mandatory actions for 

continued airworthiness. Failure to 

accomplish these actions could result in an 

unsafe condition. 

EASA previously issued AD 2016–0125, 

requiring the actions described in ALS Part 

2, Report SE–623 at issue 15 and 16. 


rmajette on DSKBCKNHB2PROD with PROPOSALS