Federal Register / Vol. 81, No. 84 / Monday, May 2, 2016 / Rules and Regulations 26121 

Issued in Renton, Washington, on April 13, 

2016. 

Victor Wicklund, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–09119 Filed 4–29–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–3988; Directorate 

Identifier 2015–NM–005–AD; Amendment 

39–18491; AD 2016–08–15] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2014–17– 

51 for certain Bombardier, Inc. Model 

CL–600–2B16 airplanes. AD 2014–17– 

51 required inspecting the inboard flap 

fasteners of the hinge-box forward 

fitting at Wing Station (WS) 76.50 and 

WS 127.25 to determine the orientation 

and condition of the fasteners, as 

applicable, and replacement or 

repetitive inspections of the fasteners if 

necessary. AD 2014–17–51 also 

provided for optional terminating action 

for the requirements of that AD. This 

new AD requires accomplishment of the 

previously optional terminating action. 

This AD was prompted by a 

determination that that additional 

action is necessary. We are issuing this 

AD to detect and correct incorrectly 

oriented or fractured fasteners, that 

could result in premature failure of the 

fasteners attaching the inboard flap 

hinge-box forward fitting; failure of the 

fasteners could lead to the detachment 

of the flap hinge box and the flap 

surface, and consequent loss of control 

of the airplane. 

DATES: This AD is effective June 6, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of June 6, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of November 12, 2014 (79 FR 

64088, October 28, 2014). 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of March 6, 2014 (79 FR 

9389, February 19, 2014). 

ADDRESSES: For service information 

identified in this final rule, 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. It is also available 

on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

3988. 

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– 

3988; 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 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, Propulsion 

and Services Branch, ANE–173, FAA, 

New York Aircraft Certification Office 

(ACO), 1600 Stewart Avenue, Suite 410, 

Westbury, NY 11590; telephone 516– 

228–7329; fax 516–794–5531. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2014–17–51, 

Amendment 39–17999 (79 FR 64088, 

October 28, 2014) (‘‘AD 2014–17–51’’). 

AD 2014–17–51 applied to certain 

Bombardier, Inc. Model CL–600–2B16 

airplanes. The NPRM published in the 

Federal Register on October 19, 2015 

(80 FR 63141) (‘‘the NPRM’’). 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2014–27R1, 

dated August 29, 2014 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for certain Bombardier, Inc. Model CL– 

600–2B16 airplanes. The MCAI states: 

There have been three in-service reports on 

604 Variant aeroplanes of a fractured fastener 

head on the inboard flap hinge-box forward 

fitting at Wing Station (WS) 76.50, found 

during a routine maintenance inspection. 

Investigation revealed that the installation of 

these fasteners on the inboard flap hinge-box 

forward fittings at WS 76.50 and WS 127.25, 

on both wings, does not conform to the 

engineering drawings. Incorrect installation 

may result in premature failure of the 

fasteners attaching the inboard flap hinge-box 

forward fitting. Failure of the fasteners could 

lead to the detachment of the flap hinge box 

and consequently the detachment of the flap 

surface. The loss of a flap surface could 

adversely affect the continued safe operation 

of the aeroplane. 

The original issue of [Canadian] AD CF– 

2013–39 [http://www.regulations.gov/

#!documentDetail;D=FAA-2014-0054-0002] 

[which corresponds to FAA AD 2014–03–17, 

Amendment 39–17754 (79 FR 9389, February 

19, 2014)] mandated a detailed visual 

inspection (DVI) of each inboard flap hingebox forward fitting, on both wings, and 

rectification as required. Incorrectly oriented 

fasteners require repetitive inspections until 

the terminating action is accomplished. 

After the issuance of [Canadian] AD CF– 

2013–39, there has been one reported 

incident on a 604 Variant aeroplane where 

four fasteners were found fractured on the 

same flap hinge-box forward fitting. The 

investigation determined that the fasteners 

were incorrectly installed. 

The original issue of this [Canadian] AD 

was issued to reduce the initial and repetitive 

inspection intervals previously mandated in 

[Canadian] AD CF–2013–39, and to impose 

replacement of the incorrectly oriented 

fasteners within 24 months. The CL–600– 

1A11, –2A12 and –2B16 (601–3A/–3R 

Variant) aeroplanes are addressed through 

[Canadian] AD CF–2013–39R1. 

Revision 1 of this [Canadian] AD is issued 

to clarify the requirements for the initial and 

repetitive inspections. 

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–2015– 

3988. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Change to Paragraph (k) of This AD 

Paragraph (k) of the NPRM specified 

to do the replacement on ‘‘both’’ wings. 

However, the replacement only needs to 

be done on the affected wing on which 

incorrectly oriented fasteners were 

found but none were found to be 

fractured. We have revised paragraph (k) 

of this AD to specify accomplishing the 

replacement on the affected wings. We 

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26122 Federal Register / Vol. 81, No. 84 / Monday, May 2, 2016 / Rules and Regulations 

have coordinated this change with 

TCCA. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting this AD 

with the change 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 Alert Service 

Bulletins: 

• A604–57–006, Revision 04, dated 

November 12, 2014, including 

Appendices 1 and 2, dated September 

26, 2013; and 

• A605–57–004, Revision 04, dated 

November 12, 2014, including 

Appendices 1 and 2, dated September 

26, 2013. 

The service information describes 

repetitive detailed visual inspections of 

each inboard flap fastener of the hingebox forward fitting at WS 76.50 and WS 

127.25, on both wings, and, if necessary, 

replacement of the fasteners. This 

service information is reasonably 

available because the interested parties 

have access to it through their normal 

course of business or by the means 

identified in the ADDRESSES section. 

Costs of Compliance 

We estimate that this AD affects 285 

airplanes of U.S. registry. 

The actions required by AD 2014–17– 

51, and retained in this AD take about 

1 work-hour per product, at an average 

labor rate of $85 per work-hour. 

Required parts cost about $0 per 

product. Based on these figures, the 

estimated cost of the actions that are 

required by AD 2014–17–51 is $85 per 

product. 

We also estimate that it will take 

about 58 work-hours per product to 

comply with the basic requirements of 

this AD. The average labor rate is $85 

per work-hour. Required parts cost 

about $753 per product. Based on these 

figures, we estimate the cost of this AD 

on U.S. operators to be $1,619,655, or 

$5,683 per product. 

In addition, we estimate that any 

necessary follow-on actions will take 

about 58 work-hours and require parts 

costing $753, for a cost of $5,683 per 

product. We have no way of 

determining the number of aircraft that 

might need this action. 

According to the manufacturer, some 

of the costs of this 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 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 

removing Airworthiness Directive (AD) 

2014–17–51, Amendment 39–17999 (79 

FR 64088, October 28, 2014), and 

adding the following new AD: 

2016–08–15 Bombardier, Inc.: Amendment 

39–18491. Docket No. FAA–2015–3988; 

Directorate Identifier 2015–NM–005–AD. 

(a) Effective Date 

This AD is effective June 6, 2016. 

(b) Affected ADs 

(1) This AD replaces AD 2014–17–51, 

Amendment 39–17999 (79 FR 64088, October 

28, 2014) (‘‘AD 2014–17–51’’). 

(2) This AD affects AD 2014–03–17, 

Amendment 39–17754 (79 FR 9389, February 

19, 2014) (‘‘AD 2014–03–17’’), only for the 

airplanes identified in paragraph (c) of this 

AD. 

(c) Applicability 

This AD applies to Bombardier, Inc. Model 

CL–600–2B16 airplanes, certificated in any 

category, serial numbers 5301 through 5665 

inclusive, and 5701 through 5920 inclusive. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Reason 

This AD was prompted by reports of 

fractured fastener heads on the inboard flap 

hinge-box forward fitting at Wing Station 

(WS) 76.50 due to incorrect installation. We 

are issuing this AD to detect and correct 

incorrectly oriented or fractured fasteners, 

that could result in premature failure of the 

fasteners attaching the inboard flap hinge-box 

forward fitting; failure of the fasteners could 

lead to the detachment of the flap hinge box 

and the flap surface, and consequent loss of 

control of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Inspection, With New Service 

Information: Airplanes Not Previously 

Inspected 

This paragraph restates the requirements of 

paragraph (g) of AD 2014–17–51, with new 

service information. For airplanes on which 

the actions required by AD 2014–03–17 have 

not been done as of November 12, 2014 (the 

effective date of AD 2014–17–51): Within 10 

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Federal Register / Vol. 81, No. 84 / Monday, May 2, 2016 / Rules and Regulations 26123 

flight cycles after November 12, 2014, or 

within 100 flight cycles after March 6, 2014 

(the effective date of AD 2014–03–17), 

whichever occurs first, do a detailed visual 

inspection of each inboard flap fastener of 

the hinge-box forward fitting at WS 76.50 and 

WS 127.25, on both wings, to determine if 

the fasteners are correctly oriented and intact 

(non-fractured, with intact fastener head). Do 

the inspection in accordance with the 

Accomplishment Instructions of Bombardier 

Alert Service Bulletin A604–57–006, 

Revision 01, dated September 26, 2013, 

including Appendices 1 and 2, dated 

September 26, 2013, Revision 02, dated 

January 22, 2014, including Appendices 1 

and 2, dated September 26, 2013, or Revision 

04, dated November 12, 2014, including 

Appendices 1 and 2, dated September 26, 

2013 (for serial numbers 5301 through 5665 

inclusive); or Bombardier Alert Service 

Bulletin A605–57–004, Revision 01, dated 

September 26, 2013, including Appendices 1 

and 2, dated September 26, 2013, Revision 

02, dated January 22, 2014, including 

Appendices 1 and 2, dated September 26, 

2013, or Revision 04, dated November 12, 

2014, including Appendices 1 and 2, dated 

September 26, 2013 (for serial numbers 5701 

through 5920 inclusive). As of the effective 

date of this AD, only use Bombardier Alert 

Service Bulletin A604–57–006, Revision 04, 

dated November 12, 2014, including 

Appendices 1 and 2, dated September 26, 

2013; or Bombardier Alert Service Bulletin 

A605–57–004, Revision 04, dated November 

12, 2014, including Appendices 1 and 2, 

dated September 26, 2013; as applicable; for 

the actions required by this paragraph. 

(1) If all fasteners are found intact and 

correctly oriented, no further action is 

required by this AD. 

(2) If any fastener is found fractured: Before 

further flight, remove and replace all forward 

and aft fasteners at WS 76.50 and WS 127.25, 

regardless of condition or orientation, on 

both wings, in accordance with the 

Accomplishment Instructions of the 

applicable service information identified in 

paragraph (g) of this AD. As of the effective 

date of this AD, only use Bombardier Alert 

Service Bulletin A604–57–006, Revision 04, 

dated November 12, 2014, including 

Appendices 1 and 2, dated September 26, 

2013; or Bombardier Alert Service Bulletin 

A605–57–004, Revision 04, dated November 

12, 2014, including Appendices 1 and 2, 

dated September 26, 2013; as applicable; for 

the actions required by this paragraph. After 

replacement of all fasteners as required by 

this paragraph of this AD, no further action 

is required by this AD. 

(3) If any incorrectly oriented but intact 

fastener is found, and no fractured fastener 

is found, repeat the inspection required by 

paragraph (g) of this AD thereafter at 

intervals not to exceed 10 flight cycles, until 

the requirements of paragraph (i)(1) or (k) of 

this AD have been done. 

(h) Retained Actions, With New Service 

Information: Airplanes Previously 

Inspected, Having Incorrectly Oriented 

Fastener(s) 

This paragraph restates the requirements of 

paragraph (h) of AD 2014–17–51, with new 

service information. For airplanes on which 

an inspection required by paragraph (g) or (j) 

of AD 2014–03–17 has been done as of 

November 12, 2014 (the effective date of AD 

2014–17–51), and on which any incorrectly 

oriented fastener, but no fractured fastener, 

was found: Except as provided by paragraph 

(i)(3) of this AD, do a detailed visual 

inspection of all inboard flap fasteners of the 

hinge-box forward fitting at WS 76.50 and 

WS 127.25, on both wings, to determine if 

the fasteners are intact (non-fractured, with 

intact fastener head). Inspect within 10 flight 

cycles after November 12, 2014, or within 

100 flight cycles after the most recent 

inspection done as required by AD 2014–03– 

17, whichever occurs first. Inspect in 

accordance with the Accomplishment 

Instructions of the applicable service 

information identified in paragraph (g) of this 

AD. As of the effective date of this AD, only 

use Bombardier Alert Service Bulletin A604– 

57–006, Revision 04, dated November 12, 

2014, including Appendices 1 and 2, dated 

September 26, 2013; or Bombardier Alert 

Service Bulletin A605–57–004, Revision 04, 

dated November 12, 2014, including 

Appendices 1 and 2, dated September 26, 

2013; as applicable; for the actions required 

by this paragraph. 

(1) If all fasteners are found intact, repeat 

the inspection thereafter at intervals not to 

exceed 10 flight cycles, until the 

requirements of paragraph (i)(1) or (k) of this 

AD have been done. 

(2) If any fastener is found fractured: Before 

further flight, remove and replace all forward 

and aft fasteners at WS 76.50 and WS 127.25, 

regardless of condition or orientation, on 

both wings, in accordance with the 

Accomplishment Instructions of the 

applicable service information identified in 

paragraph (g) of this AD. As of the effective 

date of this AD, only use Bombardier Alert 

Service Bulletin A604–57–006, Revision 04, 

dated November 12, 2014, including 

Appendices 1 and 2, dated September 26, 

2013; or Bombardier Alert Service Bulletin 

A605–57–004, Revision 04, dated November 

12, 2014, including Appendices 1 and 2, 

dated September 26, 2013; as applicable; for 

the actions required by this paragraph. After 

replacement of all fasteners as required by 

this paragraph, no further action is required 

by this AD. 

(i) Retained Terminating Action, With New 

Service Information 

This paragraph restates the terminating 

action specified in paragraph (i) of AD 2014– 

17–51), with new service information. 

(1) Replacement of all forward and aft 

fasteners at WS 76.50 and WS 127.25, on 

both wings, in accordance with the 

Accomplishment Instructions of the 

applicable service information identified in 

paragraph (g) of this AD, terminates the 

requirements of this AD. As of the effective 

date of this AD, only use Bombardier Alert 

Service Bulletin A604–57–006, Revision 04, 

dated November 12, 2014, including 

Appendices 1 and 2, dated September 26, 

2013; or Bombardier Alert Service Bulletin 

A605–57–004, Revision 04, dated November 

12, 2014, including Appendices 1 and 2, 

dated September 26, 2013; as applicable; for 

the actions specified in this paragraph. 

(2) Accomplishment of the applicable 

requirements of this AD constitutes 

terminating action for the requirements of AD 

2014–03–17 for that airplane only. 

(3) Replacement of all fractured and 

incorrectly oriented fasteners before 

November 12, 2014 (the effective date of AD 

2014–17–51), as provided by paragraph (i) or 

(k) of AD 2014–03–17, is acceptable for 

compliance with the requirements of this AD. 

(j) Retained Special Flight Permit 

Prohibition 

This paragraph restates the requirements of 

paragraph (j) of AD 2014–17–51. Special 

flight permits to operate the airplane to a 

location where the airplane can be repaired 

in accordance with 14 CFR 21.197 and 

21.199 are not allowed. 

(k) New Requirement of This AD: PostInspection Fastener Replacement 

For airplanes on which incorrectly 

oriented fasteners were found during any 

inspection required by paragraph (g), (g)(3), 

(h), or (h)(1) of this AD, but none were found 

to be fractured: Within 24 months after the 

effective date of this AD, remove and replace 

all forward and aft fasteners at WS 76.50 and 

WS 127.25, regardless of condition or 

orientation, on affected wings, in accordance 

with the Accomplishment Instructions of 

Bombardier Alert Service Bulletin A604–57– 

006, Revision 04, dated November 12, 2014, 

including Appendices 1 and 2, dated 

September 26, 2013 (for serial numbers 5301 

through 5665 inclusive); or Bombardier Alert 

Service Bulletin A605–57–004, Revision 04, 

dated November 12, 2014, including 

Appendices 1 and 2, dated September 26, 

2013 (for serial numbers 5701 through 5920 

inclusive). Accomplishing the requirements 

of this paragraph terminates the requirements 

of this AD. 

(l) Credit for Previous Actions 

(1) This paragraph provides credit for 

actions required by paragraphs (g), (h), and 

(i)(1) of this AD, if those actions were 

performed before the effective date of this AD 

using the applicable service information 

identified in paragraphs (l)(1)(i) and (l)(1)(ii) 

of this AD, which are not incorporated by 

reference in this AD. 

(i) Bombardier Alert Service Bulletin 

A604–57–006, Revision 03, dated August 19, 

2014, including Appendices 1 and 2, dated 

September 26, 2013. 

(ii) Bombardier Alert Service Bulletin 

A605–57–004, Revision 03, dated August 19, 

2014, including Appendices 1 and 2, dated 

September 26, 2013. 

(2) This paragraph provides credit for 

actions required by paragraph (k) of this AD, 

if those actions were done before the effective 

date of this AD using the applicable service 

information identified in paragraphs (l)(2)(i) 

through (l)(2)(iv) of this AD. 

(i) Bombardier Alert Service Bulletin 

A604–57–006, Revision 01, dated September 

26, 2013, including Appendices 1 and 2, 

dated September 26, 2013, which is 

incorporated by reference in AD 2014–03–17. 

(ii) Bombardier Alert Service Bulletin 

A604–57–006, Revision 02, dated January 22, 

2014, including Appendices 1 and 2, dated 

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26124 Federal Register / Vol. 81, No. 84 / Monday, May 2, 2016 / Rules and Regulations 

September 26, 2013, which was incorporated 

by reference in AD 2014–17–51. 

(iii) Bombardier Alert Service Bulletin 

A605–57–004, Revision 01, dated September 

26, 2013, including Appendices 1 and 2, 

dated September 26, 2013, which is 

incorporated by reference in AD 2014–03–17. 

(iv) Bombardier Alert Service Bulletin 

A604–57–004, Revision 02, dated January 22, 

2014, including Appendices 1 and 2, dated 

September 26, 2013, which was incorporated 

by reference in AD 2014–17–51. 

(m) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

Certification Office (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 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. 

(i) 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. 

(ii) AMOCs previously approved for AD 

2014–17–51 are acceptable for the 

corresponding requirements of 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, 

Engine and Propeller Directorate, 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. 

(n) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Emergency Airworthiness Directive CF– 

2014–27R1, dated August 29, 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–2015–3988. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (o)(6) and (o)(7) 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. 

(3) The following service information was 

approved for IBR on June 6, 2016. 

(i) Bombardier Alert Service Bulletin 

A604–57–006, Revision 04, dated November 

12, 2014, including Appendices 1 and 2, 

dated September 26, 2013. 

(ii) Bombardier Alert Service Bulletin 

A605–57–004, Revision 04, dated November 

12, 2014, including Appendices 1 and 2, 

dated September 26, 2013. 

(4) The following service information was 

approved for IBR on November 12, 2014 (79 

FR 64088, October 28, 2014). 

(i) Bombardier Alert Service Bulletin 

A604–57–006, Revision 02, dated January 22, 

2014, including Appendices 1 and 2, dated 

September 26, 2013. 

(ii) Bombardier Alert Service Bulletin 

A605–57–004, Revision 02, dated January 22, 

2014, including Appendices 1 and 2, dated 

September 26, 2013. 

(5) The following service information was 

approved for IBR on March 6, 2014 (79 FR 

9389, February 19, 2014). 

(i) Bombardier Alert Service Bulletin 

A604–57–006, Revision 01, dated September 

26, 2013, including Appendices 1 and 2, 

dated September 26, 2013. 

(ii) Bombardier Alert Service Bulletin 

A605–57–004, Revision 01, dated September 

26, 2013, including Appendices 1 and 2, 

dated September 26, 2013. 

(6) For service information identified in 

this 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. 

(7) 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. 

(8) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on April 8, 

2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–08959 Filed 4–29–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–1130; Directorate 

Identifier 2015–CE–008–AD; Amendment 

39–18492; AD 2015–09–04 R1] 

RIN 2120–AA64 

Airworthiness Directives; DG 

Flugzeugbau GmbH Gliders 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are revising Airworthiness 

Directive (AD) 2015–09–04 for DG 

Flugzeugbau GmbH Model DG–1000T 

gliders equipped with a Solo 

Kleinmotoren Model 2350 C engine. 

This AD results from mandatory 

continuing airworthiness information 

(MCAI) issued by an aviation authority 

of another country to identify and 

correct an unsafe condition on an 

aviation product. The MCAI describes 

the unsafe condition as engine shaft 

failure and consequent propeller 

detachment. We are issuing this AD to 

require actions to address the unsafe 

condition on these products. 

DATES: This AD is effective June 6, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of June 6, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of May 26, 2015 (80 FR 

25591, May 5, 2015). 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

1130; or in person at the 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 service information identified in 

this AD, contact Solo Kleinmotoren 

GmbH, Postfach 600152, 71050 

Sindelfingen, Germany; telephone: +49 

7031 301–0; fax: +49 7031 301–136; 

email: aircraft@solo-germany.com; 

Internet: http://aircraft.solo-online.com 

and DG Flugzeugbau GmbH, Otto 

Lilienthal Weg 2/Am Flugplatz, 76646 

Bruchsal, Germany; telephone: +49 7251 

3020–0; fax: +49 7251 3020–200; email: 

wassenaar@dg-flugzeugbau.de; Internet: 

http://www.dg-flugzeugbau.de/ 

index.php?id=1329. You may view this 

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