Federal Register / Vol. 78, No. 247 / Tuesday, December 24, 2013 / Proposed Rules 77615 

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 the 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 to the extent that it justifies 

making a regulatory distinction, 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. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this proposed AD and placed it in the 

AD docket. 

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) 

2007–19–09R1, Amendment 39–16322 

(75 FR 30687, June 2, 2010), and adding 

the following new AD: 

Turbomeca S.A.: Docket No. FAA–2007– 

27009; Directorate Identifier 2007–NE– 

02–AD. 

(a) Comments Due Date 

The FAA must receive comments on this 

AD action by February 24, 2014. 

(b) Affected ADs 

This AD supersedes AD 2007–19–09R1, 

Amendment 39–16322 (75 FR 30687, June 2, 

2010). 

(c) Applicability 

This AD applies to Turbomeca S.A. Arriel 

2B1 turboshaft engines that do not have 

modification TU157 incorporated. 

(d) Unsafe Condition 

This AD was prompted by reports of 

ruptures on hydromechanical metering unit 

(HMU) constant delta pressure valves that 

have less than 2,000 hours in service. We are 

issuing this AD to prevent failure of the 

HMU, which could lead to damage to the 

engine and damage to the aircraft. 

(e) Compliance 

Within the compliance times specified, 

replace the HMU with a part eligible for 

installation, unless already done. 

(1) HMU Operating Hours and Power 

Turbine (C2) Cycles Are Known. 

(i) If on the effective date of this AD, the 

HMU C2 cycles are less than 900, then 

replace the HMU before the HMU 

accumulates 1,000 C2 cycles or 1,500 HMU 

operating hours, whichever occurs first; 

(ii) If on the effective date of this AD, the 

HMU C2 cycles are 900 or more, then replace 

the HMU within 100 HMU C2 cycles after the 

effective date of this AD; 

(iii) Thereafter, replace the HMU at every 

1,000 HMU C2 cycles or 1,500 HMU 

operating hours, whichever comes first. 

(2) HMU Operating Hours Are Known and 

C2 Cycles Are Not Known. 

(i) If on the effective date of this AD, the 

HMU operating hours are less than 1,100, 

then replace the HMU before accumulating 

1,200 HMU operating hours; 

(ii) If on the effective date of this AD, the 

HMU operating hours are 1,100 or more, then 

replace the HMU within 100 HMU operating 

hours after the effective date of this AD; 

(iii) Thereafter, replace HMUs at every 

1,200 HMU operating hours. 

(f) Definition 

For the purposes of this AD, ‘‘HMU 

operating hours’’ or ‘‘C2 cycles’’ are defined 

as operating hours or C2 cycles since new, 

since overhaul, or since application of 

Turbomeca S.A. Service Bulletin (SB) No. 

292 73 2105, Version B, dated December 16, 

2010, or earlier version, or of Turbomeca S.A. 

Mandatory SB (MSB) No. 292 73 2818, 

Version D, dated June 24, 2013, or earlier 

version, whichever occurs later. 

(g) Optional Terminating Action 

Incorporation of Turbomeca S.A. SB No. 

292 73 2157, Version C, dated July 17, 2013, 

or earlier version, is terminating action to the 

replacement and repetitive inspection 

requirements of this AD. 

(h) Credit for Previous Actions 

If you performed the actions required by 

paragraphs (e)(1) or (e)(2) of this AD using an 

earlier version of Turbomeca S.A. MSB No. 

292 73 2818, Version D, dated June 24, 2013, 

you met the requirements of this AD. 

However, you must still repetitively replace 

the HMU as required by paragraphs (e)(1)(iii) 

and (e)(2)(iii) of this AD. 

(i) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

FAA, may approve AMOCs to this AD. Use 

the procedures found in 14 CFR 39.19 to 

make your request. 

(j) Related Information 

(1) For more information about this AD, 

contact Frederick Zink, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7779; fax: 781–238–7199; 

email: frederick.zink@faa.gov. 

(2) Refer to MCAI European Aviation 

Safety Agency Airworthiness Directive 2013– 

0171, dated July 30, 2013. You may examine 

the AD on the Internet at http://

www.regulations.gov by searching for and 

locating it in Docket No. FAA–2007–27009. 

(3) Turbomeca S.A. MSB No. 292 73 2818, 

Version D, dated June 24, 2013 and 

Turbomeca S.A. SB No. 292 73 2157, Version 

C, dated July 17, 2013, and Turbomeca S.A. 

SB No. 292 73 2105, Version B, dated 

December 16, 2010, pertain to the subject of 

this AD and can be obtained from Turbomeca 

S.A. using the contact information in 

paragraph (j)(4) of this AD. 

(4) For service information identified in 

this AD, contact Turbomeca, S.A., 40220 

Tarnos, France; phone: 33 (0)5 59 74 40 00; 

telex: 570 042; fax: 33 (0)5 59 74 45 1. 

(5) 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. 

Issued in Burlington, Massachusetts, on 

December 11, 2013. 

Robert J. Ganley, 

Acting Assistant Directorate Manager, Engine 

& Propeller Directorate, Aircraft Certification 

Service. 

[FR Doc. 2013–30488 Filed 12–23–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–1029; Directorate 

Identifier 2013–NM–177–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) 2010–13– 

04, which applies to certain 

Bombardier, Inc. Model DHC–8–400 

series airplanes. AD 2010–13–04 

requires modifying the nose landing 

gear (NLG) trailing arm. Since we issued 

AD 2010–13–04, we received a report of 

several missing or damaged pivot pin 

retention bolts. This proposed AD 

would require installing a new pivot pin 

retention mechanism. This proposed AD 

would also add airplanes to the 

applicability. We are proposing this AD 

to prevent failure of the pivot pin 

retention bolt, which could result in a 


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77616 Federal Register / Vol. 78, No. 247 / Tuesday, December 24, 2013 / Proposed Rules 

loss of directional control or loss of a 

NLG tire during take-off or landing. 

DATES: We must receive comments on 

this proposed AD by February 7, 2014. 

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., Q-Series Technical Help Desk, 123 

Garratt Boulevard, Toronto, Ontario 

M3K 1Y5, Canada; telephone 416–375– 

4000; fax 416–375–4539; email 

thd.qseries@aero.bombardier.com; 

Internet http://www.bombardier.com. 

You may review copies of the 

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; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this proposed AD, the MCAI, 

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: 

Ricardo Garcia, Aerospace Engineer, 

Airframe and Mechanical Systems 

Branch, ANE–171, FAA, New York 

Aircraft Certification Office, 1600 

Stewart Avenue, Suite 410, Westbury, 

New York 11590; telephone (516) 228– 

7331; 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–2013–1029; Directorate Identifier 

2013–NM–177–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 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

On June 10, 2010, we issued AD 

2010–13–04, Amendment 39–16335 (75 

FR 35622, June 23, 2010). AD 2010–13– 

04 requires actions intended to address 

an unsafe condition on the products 

listed above. 

Since we issued AD 2010–13–04, 

Amendment 39–16335 (75 FR 35622, 

June 23, 2010), Transport Canada Civil 

Aviation (TCCA), which is the aviation 

authority for Canada, has issued 

Canadian Airworthiness Directive CF– 

2009–29R1, dated August 14, 2013 

(referred to after this as the Mandatory 

Continuing Airworthiness Information, 

or ‘‘the MCAI’’), to correct an unsafe 

condition for the specified products. 

The MCAI states: 

Two in-service incidents have been 

reported on DHC–8 Series 400 aircraft in 

which the nose landing gear (NLG) trailing 

arm pivot pin retention bolt (part number 

NAS6204–13D) was damaged. One incident 

involved the left hand NLG tire which 

ruptured on take-off. Investigation 

determined that the retention bolt failure was 

due to repeated contact of the castellated nut 

with the towing device including both the 

towbar and the towbarless rigs. The loss of 

the retention bolt allowed the pivot pin to 

migrate from its normal position and resulted 

in contact with and rupture of the tire. The 

loss of the pivot pin could compromise 

retention of the trailing arm and could result 

in a loss of directional control due to loss of 

nose wheel steering. The loss of an NLG tire 

or the loss of directional control could 

adversely affect the aircraft during take off or 

landing. 

To prevent the potential failure of the pivot 

pin retention bolt, Bombardier Aerospace has 

developed a modification which includes a 

new retention bolt, a reverse orientation of 

the retention bolt and a rework of the weight 

on wheel (WOW) proximity sensor cover to 

provide clearance for the re-oriented 

retention bolt. 

Since the original issue of this [Canadian] 

AD [which corresponds to AD 2010–13–04, 

Amendment 39–16335 (75 FR 35622, June 

23, 2010)], there have been several reports of 

pivot pin retention bolts found missing or 

damaged. Additional investigation 

determined that the failures were caused by 

high contact stresses on the retention bolt 

due to excessive frictional torque on the 

pivot pin and an adverse tolerance condition 

at the retention bolt. 

Revision 1 of this [Canadian] AD mandates 

the installation of a new pivot pin retention 

mechanism. 

This proposed AD would also add 

airplanes to the applicability. AD 2010– 

13–04, Amendment 39–16335 (75 FR 

35622, June 23, 2010), affected Model 

DHC–8–400 series airplanes, serial 

numbers 4001, 4003, 4004, 4006, and 

4008 through 4238 inclusive. This 

proposed AD would affect serial 

numbers 4001 through 4435 inclusive. 

You may examine the MCAI in the AD 

docket on the Internet at http://

www.regulations.gov by searching for 

and locating it in Docket No. FAA– 

2013–1029. 

Relevant Service Information 

Bombardier, Inc. has issued Service 

Bulletin 84–32–110, Revision A, dated 

April 8, 2013. The actions described in 

this service information are intended to 

correct the unsafe condition identified 

in the MCAI. 

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 the same 

type design. 

Costs of Compliance 

We estimate that this proposed AD 

affects 383 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 


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Federal Register / Vol. 78, No. 247 / Tuesday, December 24, 2013 / Proposed Rules 77617 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Modification of the NLG trailing arm [retained actions from 

AD 2010-13-04, Amendment 39-16335 (75 FR 35622, 

June 23, 2010)].

3 work-hours × $85 per hour 

= $255.

$100 $355 $22,365 

Installation of new pivot pin retention mechanism [new proposed action].2 work-hours × $85 per hour 

= $170.

None 170 65,110 

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 proposed 

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. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this proposed AD and placed it in the 

AD docket. 

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) 

2010–13–04, Amendment 39–16335 (75 

FR 35622, June 23, 2010), and adding 

the following new AD: 

Bombardier, Inc.: Docket No. FAA–2013– 

1029; Directorate Identifier 2013–NM– 

177–AD. 

(a) Comments Due Date 

We must receive comments by February 7, 

2014. 

(b) Affected ADs 

This AD supersedes AD 2010–13–04, 

Amendment 39–16335 (75 FR 35622, June 

23, 2010). 

(c) Applicability 

This AD applies to Bombardier, Inc. Model 

DHC–8–400, –401, and –402 airplanes, 

certificated in any category, serial numbers 

4001 through 4435 inclusive. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 32, Landing Gear. 

(e) Reason 

This AD was prompted by a report of 

several missing or damaged pivot pin 

retention bolts. We are issuing this AD to 

prevent failure of the pivot pin retention bolt, 

which could result in a loss of directional 

control or a NLG tire during take-off or 

landing. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Retained Actions and Compliance 

This paragraph restates the requirements of 

paragraph (f)(1) of AD 2010–13–04, 

Amendment 39–16335 (75 FR 35622, June 

23, 2010), with no changes. For airplanes 

having serial numbers 4001, 4003, 4004, 

4006, and 4008 through 4238 inclusive: 

Within 2,000 flight hours after July 28, 2010 

(the effective date of AD 2010–13–04), 

modify the NLG trailing arm by incorporating 

Bombardier Modification Summary 4– 

113599, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–32–65, Revision A, dated 

March 2, 2009. 

(h) New Requirement of This AD: Installing 

a New Pivot Pin Retention Mechanism 

For airplanes having serial numbers 4001 

through 4435 inclusive: Within 6,000 flight 

hours or 36 months after the effective date of 

this AD, whichever occurs first, install a new 

pivot pin retention mechanism by 

incorporating Bombardier Modification 

Summary 4–113749, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–32–110, Revision A, 

dated April 8, 2013. 

(i) Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(1) This paragraph provides credit for 

actions required by paragraph (g) of this AD, 

if those actions were performed before July 

28, 2010 (the effective date of AD 2010–13– 

04, Amendment 39–16335 (75 FR 35622, 

June 23, 2010)), using the Accomplishment 

Instructions of Bombardier Service Bulletin 

84–32–65, dated December 17, 2008, which 

is not incorporated by reference in this AD. 

(2) This paragraph provides credit for 

actions required by paragraph (h) of this AD, 

if those actions were performed before the 

effective date of this AD using Bombardier 

Service Bulletin 84–32–110, dated December 

21, 2012, which is not incorporated by 

reference in this AD. 

(j) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, ANE–170, New York 

Aircraft Certification Office (ACO), FAA, has 


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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. 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) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer, use these actions if they are 

FAA-approved. Corrective actions are 

considered FAA-approved if they were 

approved by the State of Design Authority (or 

its delegated agent, or by the DAH with a 

State of Design Authority’s design 

organization approval). For a repair method 

to be approved, the repair approval must 

specifically refer to this AD. You are required 

to ensure the product is airworthy before it 

is returned to service. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2009–29R1, 

dated August 14, 2013, 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 it in Docket No. FAA–2013–1029. 

(2) For service information identified in 

this AD, contact Bombardier, Inc., Q-Series 

Technical Help Desk, 123 Garratt Boulevard, 

Toronto, Ontario M3K 1Y5, Canada; 

telephone 416–375–4000; fax 416–375–4539; 

email thd.qseries@aero.bombardier.com; 

Internet http://www.bombardier.com. You 

may review copies of 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, 2013. 

John P. Piccola, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–30468 Filed 12–23–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–1057; Directorate 

Identifier 2013–CE–041–AD] 

RIN 2120–AA64 

Airworthiness Directives; M7 

Aerospace LLC Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all M7 

Aerospace LLC Models SA226–AT, 

SA226–T, SA226–T(B), SA226–TC, 

SA227–AC (C–26A), SA227–AT, 

SA227–BC (C–26A), SA227–CC, SA227– 

DC (C–26B), SA227–TT, SA26–AT, and 

SA26–T airplanes. This proposed AD 

was prompted by reports of airplanes 

with multiple fatigue cracks in the FS 

69.31 front pressure bulkhead. This 

proposed AD would require repetitively 

inspecting (visually) the FS 51.31 front 

pressure bulkhead on SA26 series 

airplanes and FS 69.31 front pressure 

bulkhead on SA226 and SA227 series 

airplanes for cracks, and repairing any 

cracked bulkhead. This proposed AD 

also requires reporting certain 

inspection results to M7 Aerospace LLC. 

We are proposing this AD to correct the 

unsafe condition on these products. 

DATES: We must receive comments on 

this proposed AD by February 7, 2014. 

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 proposed AD, contact M7 

Aerospace LP, 10823 NE Entrance Road, 

San Antonio, Texas 78216; phone: (210) 

824–9421; fax: (210) 804–7766; Internet: 

http://www.m7aerospace.com; email: 

none. 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://

www.regulations.gov by searching and 

locating Docket Number FAA–2013– 

1057; 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 Office 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

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: 

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– 

2013–1057; Directorate Identifier 2013– 

CE–041–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 because of 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 proposed AD. 

Discussion 

We received reports of two M7 

Aerospace LLC Model SA227 airplanes 

with multiple fatigue cracks in the FS 

69.31 front pressure bulkhead. The 

cracks are located in the radii of the lefthand and right-hand part number 27– 

21027 frames. The cracks were 

discovered by maintenance personnel 

after the flight crew reported trouble 

maintaining normal cabin pressure. The 

root cause for multiple site fatigue 

cracking is the normal ground-airground pressure cycles. 


sroberts on DSK5SPTVN1PROD with PROPOSALS