Federal Register / Vol. 80, No. 247 / Thursday, December 24, 2015 / Proposed Rules 80293 

(1) For airplanes equipped with pitot/static 

pressure head part number (P/N) DU130–24: 

Within 50 hours time-in-service (TIS) after 

the effective date of this AD and repetitively 

thereafter at intervals not to exceed 50 hours 

TIS, inspect the pitot/static pressure head for 

cracks and/or separation and perform a leak 

test following the procedures in the action 

section of Britten-Norman Service Bulleting 

SB 310, Issue 4, dated September 25, 2015. 

(2) For airplanes equipped with pitot/static 

pressure head part number (P/N) DU130–24: 

If, during an inspection or test required in 

paragraph (f)(1) of this AD discrepancies are 

found, before further flight, replace the pitot/ 

static pressure head with an airworthy part. 

(3) For airplanes equipped with pitot/static 

pressure head part number (P/N) DU130–24: 

Corrections performed on airplanes as 

required in paragraph (f)(2) of this AD do not 

constitute terminating action for the 

repetitive actions required in paragraph (f)(1) 

of this AD. 

(4) For airplanes not equipped with a pitot/ 

static pressure head P/N DU130–24 on the 

effective date of this AD: After the effective 

date of this AD, do not install a pitot/static 

pressure head P/N DU130–24. 

(g) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Office, 

FAA, has the authority to approve AMOCs 

for this AD, if requested using the procedures 

found in 14 CFR 39.19. Send information to 

ATTN: Raymond Johnston, Aerospace 

Engineer, FAA, Small Airplane Directorate, 

901 Locust, Room 301, Kansas City, Missouri 

64106; telephone: (816) 329–4159; fax: (816) 

329–3047; email: raymond.johnston@faa.gov. 

Before using any approved AMOC on any 

airplane to which the AMOC applies, notify 

your appropriate principal inspector (PI) in 

the FAA Flight Standards District Office 

(FSDO), or lacking a PI, your local FSDO. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(h) Related Information 

Refer to MCAI European Aviation Safety 

Agency (EASA) AD No.: 2015–0199, dated 

October 7, 2015, for related information. You 

may examine the MCAI on the Internet at 

http://www.regulations.gov by searching for 

and locating Docket No. FAA–2015–7777. 

For service information related to this AD, 

contact Britten-Norman Aircraft Limited, 

Commodore House, Mountbatten Business 

Centre, Millbrook Road East, Southampton 

SO15 1HY, United Kingdom; telephone: +44 

20 3371 4000; fax: +44 20 3371 4001; email: 

info@bnaircraft.com; Internet: http://

www.britten-norman.com/customer-support/. 

You may review copies of the referenced 

service information at the FAA, Small 

Airplane Directorate, 901 Locust, Kansas 

City, Missouri 64106. For information on the 

availability of this material at the FAA, call 

(816) 329–4148. 

Issued in Kansas City, Missouri, on 

December 11, 2015. 

Pat Mullen, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–31850 Filed 12–23–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–7529; Directorate 

Identifier 2014–NM–207–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 supersede 

Airworthiness Directive (AD) 2014–16– 

02, for certain Bombardier, Inc. Model 

CL–600–1A11 (CL–600) airplanes. AD 

2014–16–02 currently requires revising 

the airplane flight manual to prohibit 

thrust reverser operation, doing 

repetitive detailed inspections of both 

engine thrust reversers for cracks, and 

modifying the thrust reversers if 

necessary. The modification of the 

thrust reversers is also an optional 

terminating action for the repetitive 

inspections. Since we issued AD 2014– 

16–02, we have determined that it is 

necessary to add a requirement to repair 

or modify the thrust reversers, which 

would terminate the requirements of AD 

2014–16–02. We are proposing this AD 

to detect and correct cracks of the 

translating sleeve at the thrust reverser 

actuator attachment points, which could 

result in deployment or dislodgement of 

an engine thrust reverser in flight and 

subsequent reduced control of the 

airplane. 

DATES: We must receive comments on 

this proposed AD by February 8, 2016. 

ADDRESSES: You may send comments 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 proposed AD, contact Bombardier, 

Inc., 400 Coˆte-Vertu Road West, Dorval, 

Que ́bec H4S 1Y9, Canada; telephone: 

514–855–5000; fax: 514–855–7401; 

email: thd.crj@aero.bombardier.com; 

Internet http://www.bombardier.com. 

You may view this referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, WA. For information on 

the availability of this material at the 

FAA, call 425–227–1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

7529; 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 proposed AD, 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: 

Cesar Gomez, Aerospace Engineer, 

Airframe and Mechanical Systems 

Branch, ANE–171, FAA, New York 

Aircraft Certification Office (ACO), 1600 

Stewart Avenue, Suite 410, Westbury, 

NY 11590; telephone: 516–228–7318; 

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–2015–7529; Directorate Identifier 

2014–NM–207–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD 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 


tkelley on DSK3SPTVN1PROD with PROPOSALS
80294 Federal Register / Vol. 80, No. 247 / Thursday, December 24, 2015 / Proposed Rules 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

On August 4, 2014, we issued AD 

2014–16–02, Amendment 39–17926 (79 

FR 46968, August 12, 2014). AD 2014– 

16–02 requires actions intended to 

address an unsafe condition on certain 

Bombardier, Inc. Model CL–600–1A11 

(CL–600) airplanes. AD 2014–16–02 is 

parallel to Canadian AD CF–2014–19, 

dated June 20, 2014, which additionally 

mandated repair or modification of the 

thrust reversers. At that time, we had 

determined that the compliance time for 

that action would allow enough time to 

provide notice and opportunity for prior 

public comment on the merits of the 

actions. The preamble to AD 2014–16– 

02 indicated we were considering 

further rulemaking to require repair or 

modification of the thrust reversers. We 

now have determined that further 

rulemaking is necessary. 

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 

Mandatory Continuing Airworthiness 

Information (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 the same type design. 

Costs of Compliance 

We estimate that this proposed AD 

affects 18 airplanes of U.S. registry. 

The actions required by AD 2014–16– 

02, Amendment 39–17926 (79 FR 

46968, August 12, 2014), and retained in 

this proposed AD, take about 29 workhours per product, at an average labor 

rate of $85 per work-hour. Based on 

these figures, the estimated cost of the 

actions that are required by AD 2014– 

16–02 is $2,465 per product. 

We also estimate that it would take 

about 100 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Required 

parts would cost about $509 per 

product. Based on these figures, we 

estimate the cost of this proposed AD on 

U.S. operators to be $162,162, or $9,009 

per product. 

According to the manufacturer, some 

of the costs of this proposed AD may be 

covered under warranty, thereby 

reducing the cost impact on affected 

individuals. We do not control warranty 

coverage for affected individuals. As a 

result, we have included all costs in our 

cost estimate. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

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 

removing Airworthiness Directive (AD) 

2014–16–02, Amendment 39–17926 (79 

FR 46968, August 12, 2014), and adding 

the following new AD: 

Bombardier, Inc.: Docket No. FAA–2015– 

7529; Directorate Identifier 2014–NM–

207–AD. 

(a) Comments Due Date 

We must receive comments by February 8, 

2016. 

(b) Affected ADs 

This AD replaces AD 2014–16–02, 

Amendment 39–17926 (79 FR 46968, August 

12, 2014). 

(c) Applicability 

This AD applies to Bombardier, Inc. Model 

CL–600–1A11 (CL–600) airplanes, 

certificated in any category, serial numbers 

1004 through 1085. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 78, Engine Exhaust. 

(e) Reason 

This AD was prompted by reports of partial 

deployment of an engine thrust reverser in 

flight caused by a failure of the translating 

sleeve at the thrust reverser attachment 

points. We are issuing this AD to detect and 

correct cracks of the translating sleeve at the 

thrust reverser actuator attachment points, 

which could result in deployment or 

dislodgement of an engine thrust reverser in 

flight and subsequent reduced control of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Airplane Flight Manual (AFM) 

Revision With No Changes 

This paragraph restates the requirements of 

paragraph (g) of AD 2014–16–02, 

Amendment 39–17926 (79 FR 46968, August 

12, 2014), with no changes. Within 1 

calendar day after August 12, 2014 (the 

effective date of AD 2014–16–02): Revise the 

applicable sections of the AFM to include the 

information specified in the temporary 

revisions (TRs) identified in paragraphs 

(g)(1), (g)(2), (g)(3), and (g)(4) of this AD, as 

applicable. These TRs introduce procedures 

to prohibit thrust reverser operation. Operate 

the airplane according to the limitations and 

procedures in the TRs identified in 

paragraphs (g)(1), (g)(2), (g)(3), and (g)(4) of 

this AD, as applicable. The revision required 

by paragraph (g) of this AD may be done by 

inserting copies of the applicable TRs 

identified in paragraphs (g)(1), (g)(2), (g)(3), 


tkelley on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 80, No. 247 / Thursday, December 24, 2015 / Proposed Rules 80295 

and (g)(4) of this AD into the AFM. When 

these TRs have been included in general 

revisions of the AFM, the general revisions 

may be inserted in the AFM, provided the 

relevant information in the general revision 

is identical to that in the applicable TRs, and 

the TRs may be removed. 

(1) Canadair TR 600/29, dated June 20, 

2014, to the Canadair CL–600–1A11 AFM. 

(2) Canadair TR 600/30, dated June 6, 2014, 

to the Canadair CL–600–1A11 AFM. 

(3) Canadair TR 600–1/24, dated June 20, 

2014, to the Canadair CL–600–1A11 AFM 

(Winglets) including Erratum, Publication 

No. PSP 600–1AFM (US), TR No. 600–1/24, 

June 20, 2014. 

(4) Canadair TR 600–1/26, dated June 6, 

2014, to the Canadair CL–600–1A11 AFM 

(Winglets). 

(h) Retained Repetitive Inspections With No 

Changes 

This paragraph restates the requirements of 

paragraph (h) of AD 2014–16–02, 

Amendment 39–17926 (79 FR 46968, August 

12, 2014), with no changes. Within 25 flight 

cycles or 90 days, whichever occurs first, 

after August 12, 2014 (the effective date of 

AD 2014–16–02), do detailed inspections 

(including a borescope inspection) of both 

engine thrust reversers for cracks, in 

accordance with the Accomplishment 

Instructions of Bombardier Alert Service 

Bulletin A600–0769, Revision 01, dated June 

26, 2014. 

(1) If no cracking is found during any 

inspection required by paragraph (h) of this 

AD, repeat the inspection required by 

paragraph (h) of this AD thereafter at 

intervals not to exceed 100 flight cycles until 

the repair or modification specified in 

paragraph (i) or (k) of this AD is done. 

(2) If any cracking is found during any 

inspection required by paragraph (h) of this 

AD, before further flight, modify the thrust 

reversers on both engines, in accordance with 

the Accomplishment Instructions of 

Bombardier Alert Service Bulletin A600– 

0769, Revision 01, dated June 26, 2014. 

(i) Retained Optional Terminating 

Modification With No Changes 

This paragraph restates the requirements of 

paragraph (i) of AD 2014–16–02, Amendment 

39–17926 (79 FR 46968, August 12, 2014), 

with no changes. Modifying the thrust 

reversers on both engines, in accordance with 

the Accomplishment Instructions of 

Bombardier Alert Service Bulletin A600– 

0769, Revision 01, dated June 26, 2014, 

terminates the inspections required by 

paragraph (h) of this AD. 

(j) Retained Credit for Previous Actions With 

No Changes 

This paragraph restates the requirements of 

paragraph (j) of AD 2014–16–02, Amendment 

39–17926 (79 FR 46968, August 12, 2014), 

with no changes. This paragraph provides 

credit for actions required by paragraphs (h) 

and (i) of this AD, if those actions were 

performed before August 12, 2014 (the 

effective date of AD 2014–16–02) using 

Bombardier Alert Service Bulletin A600– 

0769, dated June 19, 2014, which is not 

incorporated by reference in this AD. 

(k) New Requirement of This AD: Repair/

Modify 

Within 24 months after the effective date 

of this AD, repair or modify the thrust 

reversers on both engines, using a method 

approved by the Manager, New York Aircraft 

Certification Office (ACO), ANE–170, FAA; 

or Transport Canada Civil Aviation (TCCA); 

or Bombardier, Inc.’s TCCA Design Approval 

Organization (DAO). Accomplishment of the 

repair or modification of all thrust reversers 

terminates the requirements of paragraphs (h) 

and (i) of this AD. 

(l) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York ACO, 

ANE–170, 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 New York ACO, send it to ATTN: 

Program Manager, Continuing Operational 

Safety, FAA, New York ACO, 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. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Contacting the Manufacturer: As of the 

effective date of this AD, 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, ANE–170, 

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

DAO. If approved by the DAO, the approval 

must include the DAO-authorized signature. 

(m) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

AD CF–2014–19, dated June 20, 2014, 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–2015–7529. 

(2) For service information identified in 

this AD, contact Bombardier, Inc., 400 CoˆteVertu Road West, Dorval, Que ́bec H4S 1Y9, 

Canada; telephone: 514–955–5000; fax: 514– 

855–7401; email: thd.crj

@aero.bombardier.com; Internet http:// 

www.bombardier.com. You may view this 

service information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue SW., 

Renton, WA. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

Issued in Renton, Washington, on 

December 11, 2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service, 

[FR Doc. 2015–32085 Filed 12–23–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0651; Directorate 

Identifier 2014–NM–043–AD] 

RIN 2120–AA64 

Airworthiness Directives; Gulfstream 

Aerospace Corporation Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Supplemental notice of 

proposed rulemaking (NPRM); 

reopening of comment period. 

SUMMARY: We are revising an earlier 

proposed airworthiness directive (AD) 

for all Gulfstream Aerospace 

Corporation Model GV and GV–SP 

airplanes. The NPRM proposed to 

supersede Airworthiness Directive (AD) 

2013–22–19, which requires inspecting 

to determine if fuel boost pumps having 

a certain part number are installed, 

replacing the fuel boost pumps having 

a certain part number, and revising the 

airplane maintenance or inspection 

program to include revised instructions 

for continued airworthiness. The NPRM 

also proposed to require revising the 

airplane maintenance program to 

include a fuel leak check of the fuel 

boost pumps, using new service 

information. The NPRM was prompted 

by reports of two independent types of 

failure of the fuel boost pump: overheat 

damage on the internal components and 

external housing, and fuel leakage. This 

action revises the NPRM by reducing 

the compliance time for revising the 

airplane maintenance program. We are 

proposing this supplemental NPRM 

(SNPRM) to prevent fuel leakage in 

combination with a capacitor clearance 

issue, which could result in an 

uncontrolled fire in the wheel well. 

Since these actions impose an 

additional burden over that proposed in 

the NPRM, we are reopening the 

comment period to allow the public the 

chance to comment on these proposed 

changes. 

DATES: We must receive comments on 

this SNPRM by February 8, 2016. 

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 


tkelley on DSK3SPTVN1PROD with PROPOSALS