42660 Federal Register / Vol. 79, No. 141 / Wednesday, July 23, 2014 / Rules and Regulations 

ACRO, G103C TWIN III ACRO and Model G 

103 C Twin III SL gliders with the following 

serial numbers (S/N), certificated in any 

category. 

(1) G102 STANDARD ASTIR III, S/N 5501 

through 5652. 

(2) G102 CLUB ASTIR III, S/N 5501 

through 5652. 

(3) G102 CLUB ASTIR IIIb, S/N 5501 

through 5652. 

(4) G103 TWIN II, S/N 3730 through 34078. 

(5) G103A TWIN II ACRO, S/N 3730 

through 34078. 

(6) G103C TWIN III ACRO, S/N 34101 

through 34203. 

(7) G 103 C Twin III SL, S/N 35002 through 

35051. 

(d) Subject 

Air Transport Association of America 

(ATA) Code 27: Flight Controls. 

(e) Reason 

This AD was prompted by mandatory 

continuing airworthiness information (MCAI) 

originated 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 plastic 

control cable pulleys developing cracks due 

to aging. We are issuing this AD to detect and 

correct plastic control cable pulleys in the 

rudder control unit, which could lead to 

breaking of the pulley and potentially 

jamming the rudder control unit, possibly 

resulting in loss of control of the glider. 

(f) Actions and Compliance 

Comply with this AD within the 

compliance times specified in paragraphs 

(f)(1) through (f)(3) of this AD, unless already 

done. 

(1) For all Models G103C TWIN III ACRO 

and G 103 C Twin III SL gliders: Within 3 

months after August 27, 2014 (the effective 

date of this AD), inspect the rudder control 

unit for installation of plastic cable pulleys. 

If plastic cable pulleys are installed, before 

further flight, replace the plastic cable 

pulleys with aluminum cable pulleys 

following the actions and instructions of 

Fiberglas-Technik Rudolf Lindner GmbH & 

Co. KG Service Bulletin SB–G05 and 

Fiberglas-Technik Rudolf Lindner GmbH & 

Co. KG Instructions A/I–G05, both dated 

January 17, 2014. 

(2) For all Models G102 STANDARD 

ASTIR III, G102 CLUB ASTIR III, G102 CLUB 

ASTIR IIIb, G103 TWIN II, and G103A TWIN 

II ACRO gliders: Within 1 month after August 

27, 2014 (the effective date of this AD), 

inspect the rudder control unit for 

installation of plastic cable pulleys. If plastic 

cable pulleys are installed, before further 

flight, replace the plastic cable pulleys with 

aluminum cable pulleys following the 

actions and instructions of Fiberglas-Technik 

Rudolf Lindner GmbH & Co. KG Service 

Bulletin SB–G05 and Fiberglas-Technik 

Rudolf Lindner GmbH & Co. KG Instructions 

A/I–G05, both dated January 17, 2014. 

(3) As of August 27, 2014 (the effective 

date of this AD), do not install any plastic 

control cable pulley in the rudder control 

unit of any glider identified in paragraphs 

(c)(1) through (c)(7) of this AD. 

(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: Jim Rutherford, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4165; fax: (816) 329– 

4090; email: jim.rutherford@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 European Aviation Safety Agency 

(EASA) AD No.: 2014–0067, dated March 18, 

2014, for related information. The MCAI can 

be found in the AD docket on the Internet at: 

http://www.regulations.gov/#!document

Detail;D=FAA-2014-0292-0002. 

(i) 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) Fiberglas-Technik Rudolf Lindner 

GmbH & Co. KG Service Bulletin SB–G05, 

dated January 17, 2014. 

(ii) Fiberglas-Technik Rudolf Lindner 

GmbH & Co. Fiberglas-Technik Rudolf 

Lindner GmbH & Co. KG Instructions A/I– 

G05, dated January 17, 2014. 

(3) For Fiberglas-Technik Rudolf Lindner 

GmbH & Co. service information identified in 

this AD, contact Fiberglas-Technik Rudolf 

Lindner GmbH & Co. KG, Steige 3, D–88487 

Walpertshofen, Germany; telephone: +49 (0) 

7353/22 43; fax: +49 (0) 7353/30 96; email: 

info@LTB-Lindner.com; Web site: http://

www.ltb-lindner.com/home.104.html. 

(4) You may view this 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. 

(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 Kansas City, Missouri, on July 14, 

2014. 

Kelly A. Broadway, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–17052 Filed 7–22–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0308; Directorate 

Identifier 2014–CE–012–AD; Amendment 

39–17903; AD 2014–15–01] 

RIN 2120–AA64 

Airworthiness Directives; M7 

Aerospace LLC Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for M7 

Aerospace LLC Models SA227–AT, 

SA227–AC, SA227–BC, SA227–CC, and 

SA227–DC airplanes equipped with a 

bayonet shear pin main cabin door 

latching mechanism. This AD was 

prompted by fatigue cracks found in the 

internal door surround doubler, the 

fuselage external skin, and the door 

corner fittings at the fuselage upper 

forward corner of the main cabin door 

cutout. This AD requires repetitively 

inspecting the four corners of the main 

cabin door cutout for cracks, making 

necessary repairs, and reporting 

inspection results to M7 Aerospace LLC. 

We are issuing this AD to correct the 

unsafe condition on these products. 

DATES: This AD is effective August 27, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of August 27, 2014. 

ADDRESSES: For service information 

identified in this AD, contact M7 

Aerospace LLC, 10823 NE Entrance 

Road, San Antonio, Texas 78216; phone: 

(210) 824–9421; fax: (210) 804–7766; 

Internet: http://www.elbitsystemsus.com; email: MetroTech@

M7Aerospace.com. You may view this 

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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

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Federal Register / Vol. 79, No. 141 / Wednesday, July 23, 2014 / Rules and Regulations 42661 

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0308; 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 (phone: 800–647–5527) is 

Document 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: 

Andrew McAnaul, Aerospace Engineer, 

FAA, ASW–150 (c/o San Antonio 

MIDO), 10100 Reunion Place, Suite 650, 

San Antonio, Texas 78216; phone: (210) 

308–3365; fax: (210) 308–3370; email: 

andrew.mcanaul@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 M7 Aerospace LLC Models 

SA227–AT, SA227–AC, SA227–BC, 

SA227–CC, and SA227–DC airplanes 

equipped with a bayonet shear pin main 

cabin door latching mechanism. The 

NPRM published in the Federal 

Register on May 14, 2014 (79 FR 27505). 

The NPRM was prompted by reports 

of fatigue cracking of the main cabin 

door surround structure. Investigation 

revealed that the fatigue cracks are 

related to a change in loading due to 

design changes in the door surround 

structure and the door latching system. 

We are issuing this AD to correct the 

unsafe condition on these products. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (79 

FR 27505, May 14, 2014) or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting this AD 

as proposed except for minor editorial. 

We have determined that these minor 

changes: 

• Are consistent with the intent that 

was proposed in the NPRM (79 FR 

27505, May 14, 2014) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (79 FR 27505, 

May 14, 2014). 

Costs of Compliance 

We estimate that this AD affects 250 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Threshold high frequency eddy current (HFEC)/low 

frequency eddy current (LFEC)/detailed visual inspection.

2.5 work-hours × $85 per 

hour = $212.50.

Not Applicable ................. $212.50 $53,125 

We estimate the following costs to do 

any necessary repairs that will be 

required based on the results of the 

inspection. We have no way of 

determining the number of aircraft that 

might need these repairs: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Repair Installation ......................................................... 48 work-hours × $85 per hour = $4,080 ...................... $6,670 $10,750 

Paperwork Reduction Act 

A federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject 

to penalty for failure to comply with a 

collection of information subject to the 

requirements of the Paperwork 

Reduction Act unless that collection of 

information displays a current valid 

OMB control number. The control 

number for the collection of information 

required by this AD is 2120–0056. The 

paperwork cost associated with this AD 

has been detailed in the Costs of 

Compliance section of this document 

and includes time for reviewing 

instructions, as well as completing and 

reviewing the collection of information. 

Therefore, all reporting associated with 

this AD is mandatory. Comments 

concerning the accuracy of this burden 

and suggestions for reducing the burden 

should be directed to the FAA at 800 

Independence Ave. SW., Washington, 

DC 20591. ATTN: Information 

Collection Clearance Officer, AES–200. 

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 

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, 

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42662 Federal Register / Vol. 79, No. 141 / Wednesday, July 23, 2014 / Rules and Regulations 

(2) Is not a ‘‘significant rule’’ under 

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): 

2014–15–01 M7 Aerospace LLC: 

Amendment 39–17903; Docket No. 

FAA–2014–0308; Directorate Identifier 

2014–CE–012–AD. 

(a) Effective Date 

This AD is effective August 27, 2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the M7 Aerospace LLC 

airplanes listed in paragraphs (c)(1) through 

(c)(5) of this AD that are equipped with a 

bayonet shear pin main cabin door latching 

mechanism and are certificated in any 

category. Airplanes equipped with a ‘‘clickclack’’ main cabin door latching mechanism 

are not affected by this AD. Figure 3 of M7 

Aerospace LLC SA227 Series Commuter 

Category Service Bulletin CC7–53–005, and 

M7 Aerospace LLC SA227 Series Service 

Bulletin 227–53–009, both dated November 

15, 2013, is a picture showing both styles of 

latching mechanisms. 

(1) Model SA227–AT airplanes, serial 

numbers (S/Ns) AT570 through AT631, and 

AT695. 

(2) Model SA227–AC airplanes, S/Ns 

AC570 through AC788. 

(3) Model SA227–BC airplanes, S/Ns 

BC762, BC764, BC766, and BC770 through 

BC789. 

(4) Model SA227–CC airplanes, S/N 

CC827, CC829, and CC840 through CC844. 

(5) Model SA227–DC airplanes, S/Ns 

DC784, DC790 through DC826, DC828, 

DC830 through DC839, and DC845 through 

DC904. 

(d) Subject 

Joint Aircraft System Component (JASC)/

Air Transport Association (ATA) of 

America—Code 5310, Fuselage Main, 

Structure. 

(e) Unsafe Condition 

This AD was prompted by fatigue cracks 

found in the internal door surround doubler, 

the external skin fuselage skin, and the door 

corner fittings at the fuselage upper forward 

corner of the main cabin door cutout. We are 

issuing the AD to prevent decompression 

failure with possible loss of structural 

integrity of the cabin structure. 

(f) Compliance 

Comply with this AD within the 

compliance times specified in paragraph (g) 

through paragraph (k) of this AD, including 

all subparagraphs, unless already done. 

(g) Inspections 

(1) Do the initial inspections of the fuselage 

upper forward corner and other 3 corners of 

the main cabin door cutout for cracks 

following Table 1 in Step 2. 

ACCOMPLISHMENT INSTRUCTIONS of M7 

Aerospace LLC SA227 Series Commuter 

Category Service Bulletin CC7–53–005 or M7 

Aerospace LLC SA227 Series Service Bulletin 

227–53–009, both dated November 15, 2013, 

as applicable. Do the inspections at the 

compliance times specified in paragraphs 

(g)(1)(i) through (g)(1)(iv) of this AD. For the 

purposes of this AD, owner/operators who do 

not track total aircraft flight cycles (TAC), use 

a .5 to 1 conversion, e.g., 35,000 TAC is 

equivalent to 17,500 hours time-in-service 

(TIS). For owner/operators who do not track 

flight cycles, use a 1 to 1 conversion, e.g., 300 

flight cycles are equivalent to 300 hours TIS. 

(i) For aircraft with more than 35,000 TAC, 

inspect within the next 300 flight cycles after 

August 27, 2014 (the effective date of this 

AD). 

(ii) For aircraft with 20,001—35,000 TAC, 

inspect within the next 600 flight cycles after 

August 27, 2014 (the effective date of this 

AD). 

(iii) For aircraft with 12,000—20,000 TAC, 

inspect within the next 1,000 flight cycles 

after August 27, 2014 (the effective date of 

this AD). 

(iv) For aircraft with less than 12,000 TAC, 

inspect at 12,000 flight cycles or within the 

next 1,000 flight cycles after August 27, 2014 

(the effective date of this AD), whichever 

occurs later. 

(2) If no cracks are found during the 

inspections required by paragraph (g)(1) of 

this AD, repetitively thereafter at intervals 

not to exceed 2,000 flight cycles do the 

inspections of the fuselage upper forward 

corner and other 3 corners of the main cabin 

door cutout for cracks following Table 1 in 

Step 2. ACCOMPLISHMENT 

INSTRUCTIONS of M7 Aerospace LLC 

SA227 Series Commuter Category Service 

Bulletin CC7–53–005 or M7 Aerospace LLC 

SA227 Series Service Bulletin 227–53–009, 

both dated November 15, 2013, as applicable. 

(h) Repair Cracks and Repetitively Inspect 

(1) If any cracks are found during any 

inspection required in paragraph (g) through 

paragraph (i) of this AD, before further flight 

after the inspection in which a crack is 

found, repair or replace the cracked structure 

following Step 3. REPAIR OF CRACKED 

INNER DOUBLE, Step 4. REPAIR OF 

CRACKED FUSELAGE SKIN, and/or Step 5. 

REPAIR OF CRACKED CORNER FITTING of 

M7 Aerospace LLC SA227 Series Commuter 

Category Service Bulletin CC7–53–005, or M7 

Aerospace LLC SA227 Series Service Bulletin 

227–53–009, both dated November 15, 2013, 

as applicable. 

(2) If you made the repairs required in 

paragraph (h)(1) of this AD by installing 

repair kit drawing 27K24191–001, do the 

threshold and repeat inspections following 

Table 2 in Step 2. ACCOMPLISHMENT 

INSTRUCTIONS of M7 Aerospace LLC 

SA227 Series Commuter Category Service 

Bulletin CC7–53–005, dated November 15, 

2013; or M7 Aerospace LLC SA227 Series 

Service Bulletin 227–53–009, dated 

November 15, 2013, as applicable. 

(3) If you made the repairs required in 

paragraph (h)(1) of this AD by replacing the 

fuselage skin by installing repair kit drawing 

27K24191–003, or if the corner fitting was 

replaced and no other cracks are present, 

repetitively thereafter inspect following 

Table 1 in Step 2. ACCOMPLISHMENT 

INSTRUCTIONS of M7 Aerospace LLC 

SA227 Series Commuter Category Service 

Bulletin CC7–53–005, or M7 Aerospace LLC 

SA227 Series Service Bulletin 227–53–009, 

both dated November 15, 2013, as applicable. 

(i) Extend Repetitive Inspection Intervals 

After any inspection required in paragraph 

(g)(1) and (g)(2) of this AD and if no damage, 

defects, or cracks are found, you may install 

repair kit drawing 27K24191–001 following 

Step 6. ADDITION OF KIT DRAWING 

REPAIR MEMBERS AS PREVENTATIVE 

ACTION of M7 Aerospace LLC SA227 Series 

Commuter Category Service Bulletin CC7– 

53–005, or M7 Aerospace LLC SA227 Series 

Service Bulletin 227–53–009, both dated 

November 15, 2013, as applicable, to extend 

the inspection intervals. After installing 

repair kit drawing 27K24191–001, do the 

threshold and repeat inspections following 

Table 3 of Step 2. ACCOMPLISHMENT 

INSTRUCTIONS of M7 Aerospace LLC 

SA227 Series Commuter Category Service 

Bulletin CC7–53–005, or M7 Aerospace LLC 

SA227 Series Service Bulletin 227–53–009, 

both dated November 15, 2013, as applicable. 

(j) Reporting Requirement 

Within 30 days after any inspection 

required by paragraph (g) through paragraph 

(i) of this AD where a crack or any other 

damage is found, report the results of that 

inspection to M7 Aerospace LLC following 

the instructions specified in Step 2.I. of the 

ACCOMPLISHMENT INSTRUCTIONS of M7 

Aerospace LLC SA227 Series Commuter 

Category Service Bulletin CC7–53–005, dated 

November 15, 2013; or Step 2.J. of the 

ACCOMPLISHMENT INSTRUCTIONS of M7 

Aerospace LLC SA227 Series Service Bulletin 

227–53–009, dated November 15, 2013, as 

applicable. 

(k) Credit for Previous Repairs 

As of August 27, 2014 (the effective date 

of this AD), owner/operators who had the an 

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Federal Register / Vol. 79, No. 141 / Wednesday, July 23, 2014 / Rules and Regulations 42663 

inspection and any resulting repairs done 

before the effective date of this AD using 

procedures different from those specified in 

M7 Aerospace LLC SA227 Series Commuter 

Category Service Bulletin CC7–53–005, dated 

November 15, 2013; and M7 Aerospace LLC 

SA227 Series Service Bulletin 227–53–009, 

dated November 15, 2013, may apply for an 

alternative method of compliance (AMOC) 

following the instructions in paragraph (m) of 

this AD. 

(l) Paperwork Reduction Act Burden 

Statement 

A federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject to 

a penalty for failure to comply with a 

collection of information subject to the 

requirements of the Paperwork Reduction 

Act unless that collection of information 

displays a current valid OMB Control 

Number. The OMB Control Number for this 

information collection is 2120–0056. Public 

reporting for this collection of information is 

estimated to be approximately 5 minutes per 

response, including the time for reviewing 

instructions, completing and reviewing the 

collection of information. All responses to 

this collection of information are mandatory. 

Comments concerning the accuracy of this 

burden and suggestions for reducing the 

burden should be directed to the FAA at: 800 

Independence Ave. SW., Washington, DC 

20591, Attn: Information Collection 

Clearance Officer, AES–200. 

(m) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Fort Worth Airplane 

Certification Office, 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 ACO, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

(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. 

(n) Related Information 

For more information about this AD, 

contact Andrew McAnaul, Aerospace 

Engineer, FAA, ASW–150 (c/o San Antonio 

MIDO), 10100 Reunion Place, Suite 650, San 

Antonio, Texas 78216; phone: (210) 308– 

3365; fax: (210) 308–3370; email: 

andrew.mcanaul@faa.gov. 

(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 the AD specifies otherwise. 

(i) M7 Aerospace LLC SA227 Series 

Commuter Category Service Bulletin CC7– 

53–005, dated November 15, 2013. 

(ii) M7 Aerospace LLC SA227 Series 

Service Bulletin 227–53–009, dated 

November 15, 2013. 

(3) For M7 Aerospace LLC service 

information identified in this AD, contact M7 

Aerospace LLC, 10823 NE Entrance Road, 

San Antonio, Texas 78216; phone: (210) 824– 

9421; fax: (210) 804–7766; Internet: http://

www.m7aerospace.com; email: MetroTech@

M7Aerospace.com. 

(4) You may view this service information 

at 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. 

(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 Kansas City, Missouri, on July 14, 

2014. 

Kelly A. Broadway, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–17053 Filed 7–22–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0159; Directorate 

Identifier 2014–NE–01–AD; Amendment 39– 

17905; AD 2014–15–03] 

RIN 2120–AA64 

Airworthiness Directives; Pratt & 

Whitney Canada Corporation 

Turboprop Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

serial number Pratt & Whitney Canada 

Corporation (P&WC) model PW150A 

turboprop engines. This AD requires 

rerouting of the igniter cables and 

installation of new support brackets. 

This AD was prompted by reports of 

damage to a high-pressure fuel line, 

which could result in a high-pressure 

fuel leak into the engine nacelle. We are 

issuing this AD to prevent high-pressure 

fuel leaks, which could cause engine 

fire and damage to the engine and the 

airplane. 

DATES: This AD becomes effective 

August 27, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of August 27, 2014. 

ADDRESSES: For service information 

identified in this AD, contact Pratt & 

Whitney Canada Corp., 1000 MarieVictorin, Longueuil, Quebec, Canada, 

J4G 1A1; phone: (800) 268–8000; fax: 

(450) 647–2888; Internet: www.pwc.ca. 

You may view this service information 

at the FAA, Engine & Propeller 

Directorate, 12 New England Executive 

Park, Burlington, MA. For information 

on the availability of this material at the 

FAA, call (781) 238–7125. 

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–2014– 

0159; 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 mandatory 

continuing airworthiness information 

(MCAI), the regulatory evaluation, any 

comments received, and other 

information. The address for the Docket 

Office (phone: (800) 647–5527) is 

Document 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: 

Wego Wang, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: (781) 238–7134; fax: (781) 238– 

7199; email: wego.wang@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 the specified products. The 

NPRM was published in the Federal 

Register on April 10, 2014 (79 FR 

19844). The NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

There have been reports of damage in 

excess of acceptable criteria to the highpressure fuel line from the P&WC PW150A 

engine flowmeter to the flow divider. Damage 

has included fretting wear through contact 

with the engine igniter cables. The contact is 

the result of incorrectly routed igniter cables. 

While there has been no report of associated 

fuel leakage, the fretting wear, if undetected, 

could progress to a point where highpressure fuel would leak into the engine 

nacelle. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comment received. 

mstockstill on DSK4VPTVN1PROD with RULES