Federal Register / Vol. 76, No. 8 / Wednesday, January 12, 2011 / Rules and Regulations 1993 

compliance with EASA AD 2007–0241R3. 

All aeroplanes which are in compliance with 

EASA AD 2007–0241R3 have to follow the 

repetitive inspection requirements as 

described in Pilatus PC–6 AMM Chapter 04– 

00–00, Document Number 01975, Revision 

12 and the Airworthiness Limitations (ALS) 

Document Number 02334 Revision 1 

mandated by EASA AD 2010–0176. 

Therefore the repetitive inspection 

requirements corresponding paragraphs have 

been deleted in this new EASA AD revision. 

The paragraph numbers of EASA AD 2007– 

0241R numbering has been maintained for 

referencing needs. 

This AD requires actions that are intended to 

address the unsafe condition described in the 

MCAI. 

Actions and Compliance 

(f) Unless already done, do the following 

actions: 

(1) For affected airplanes that have not had 

both wing strut fittings replaced within the 

last 100 hours time-in-service (TIS) before 

September 26, 2007 (the effective date of AD 

2007–19–14), or have not been inspected 

using an eddy current inspection method 

following Pilatus Aircraft Ltd. Pilatus PC–6 

Service Bulletin No. 57–004, dated April 16, 

2007, within the last 100 hours TIS before 

September 26, 2007 (the effective date of AD 

2007–19–14): Before further flight after either 

September 26, 2007 (the effective date of AD 

2007–19–14), or October 1, 2009 (the 

effective date of AD 2009–18–03), visually 

inspect the upper wing strut fittings and 

examine the spherical bearings following the 

Pilatus Aircraft Ltd. Pilatus PC–6 Service 

Bulletin No. 57–005, REV No. 2, dated May 

19, 2008. 

(2) For all affected airplanes: Within 25 

hours TIS after September 26, 2007 (the 

effective date of AD 2007–19–14), or within 

30 days after September 26, 2007 (the 

effective date of AD 2007–19–14), whichever 

occurs first, visually and using eddy current 

methods, inspect the upper wing strut fittings 

and examine the spherical bearings following 

Pilatus Aircraft Ltd. Pilatus PC–6 Service 

Bulletin No. 57–005, REV No. 2, dated May 

19, 2008. 

(3) You may also take ‘‘unless already 

done’’ credit for any inspection specified in 

paragraphs (f)(1) or (f)(2) of this AD if done 

before October 1, 2009 (the effective date 

retained from AD 2009–18–03) following 

Pilatus Aircraft Ltd. Pilatus PC–6 Service 

Bulletin No. 57–005, dated August 30, 2007; 

or Pilatus Aircraft Ltd. Pilatus PC–6 Service 

Bulletin No. 57–005, REV No. 1, dated 

November 19, 2007. 

(4) For all affected airplanes: If during any 

inspection required by paragraphs (f)(1) or 

(f)(2) of this AD you find cracks in the upper 

wing strut fitting or the spherical bearing is 

not in conformity, before further flight, 

replace the cracked upper wing strut fitting 

and/or the nonconforming spherical bearing 

following Chapter 57–00–02 of Pilatus 

Aircraft Ltd. Pilatus PC–6 Aircraft 

Maintenance Manual, dated November 30, 

2008. 

Note 1: AD 2011–01–14 requires the 

incorporation of the updated maintenance 

requirements into the airworthiness 

limitations section of the instructions for 

continued airworthiness. Those updated 

maintenance requirements include the 

repetitive inspections for the wing strut 

fittings and the spherical bearings. This 

revised AD removes those repetitive 

inspections. 

FAA AD Differences 

Note 2: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(g) 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: Doug Rudolph, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4059; fax: (816) 329– 

4090. 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. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, 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. 

Related Information 

(h) Refer to MCAI EASA AD No.: 2007– 

0241R4, dated August 31, 2010; Pilatus 

Aircraft Ltd. Pilatus PC–6 Service Bulletin 

No. 57–005, REV No. 2, dated May 19, 2008; 

Pilatus Aircraft Ltd. Pilatus PC–6 Service 

Bulletin No. 57–005, REV No. 1, dated 

November 19, 2007; Pilatus Aircraft Ltd. 

Pilatus PC–6 Service Bulletin No. 57–005, 

dated August 30, 2007; Pilatus Aircraft Ltd. 

Pilatus PC–6 Service Bulletin No. 57–004, 

dated April 16, 2007; and Chapter 57–00–02 

of Pilatus Aircraft Ltd. Pilatus PC–6 Aircraft 

Maintenance Manual, dated November 30, 

2008, for related information. 

Material Incorporated by Reference 

(h) You must use Pilatus Aircraft Ltd. 

Pilatus PC–6 Service Bulletin No. 57–005, 

REV No. 2, dated May 19, 2008; and Chapter 

57–00–02 of Pilatus Aircraft Ltd. Pilatus PC– 

6 Aircraft Maintenance Manual, dated 

November 30, 2008 (referenced as revision 9 

in EASA AD No.: 2007–0241R3), to do the 

actions required by this AD, unless the AD 

specifies otherwise. 

(1) On October 1, 2009 (74 FR 43636, 

August 27, 2009), the Director of the Federal 

Register previously approved the 

incorporation by reference of Pilatus Aircraft 

Ltd. Pilatus PC–6 Service Bulletin No. 57– 

005, REV No. 2, dated May 19, 2008; and 

Chapter 57–00–02 of Pilatus Aircraft Ltd. 

Pilatus PC–6 Aircraft Maintenance Manual, 

dated November 30, 2008 (referenced as 

revision 9 in EASA AD No.: 2007–0241R3). 

(2) For service information identified in 

this AD, contact PILATUS AIRCRAFT LTD., 

Customer Service Manager, CH–6371 

STANS, Switzerland; telephone: +41 (0) 41 

619 65 01; fax: +41 (0) 41 619 65 76; Internet: 

http://www.pilatus-aircraft.com. 

(3) 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. 

(4) You may also review copies of the 

service information incorporated by reference 

for this AD 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/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Kansas City, Missouri, on 

December 28, 2010. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2010–33333 Filed 1–11–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0549; Directorate 

Identifier 2010–NM–109–AD; Amendment 

39–16573; AD 2011–01–16] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model DC–9–81 (MD–81), 

DC–9–82 (MD–82), DC–9–83 (MD–83), 

DC–9–87 (MD–87), and MD–88 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

mstockstill on DSKH9S0YB1PROD with RULES

1994 Federal Register / Vol. 76, No. 8 / Wednesday, January 12, 2011 / Rules and Regulations 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD requires 

installing fuel level float and pressure 

switch in-line fuses on the wing forward 

spars and forward and aft auxiliary fuel 

tanks, depending on the airplane 

configuration. This AD was prompted 

by fuel system reviews conducted by the 

manufacturer. We are issuing this AD to 

prevent the potential of ignition sources 

inside fuel tanks, which, in combination 

with flammable fuel vapors, could result 

in fuel tank explosions and consequent 

loss of the airplane. 

DATES: This AD is effective February 16, 

2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of February 16, 2011. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, 3855 

Lakewood Boulevard, MC D800–0019, 

Long Beach, California 90846–0001; 

telephone 206–544–5000, extension 2; 

fax 206–766–5683; e-mail 

dse.boecom@boeing.com; Internet 

https://www.myboeingfleet.com. You 

may review copies of the referenced 

service information at the FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington. 

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 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: 

Samuel Lee, Aerospace Engineer, 

Propulsion Branch, ANM–140L, FAA, 

Los Angeles Aircraft Certification Office 

(ACO), 3960 Paramount Boulevard, 

Lakewood, California 90712–4137; 

telephone 562–627–5262; fax 562–627– 

5210; e-mail samuel.lee@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an airworthiness 

directive (AD) that would apply to the 

specified products. That NPRM was 

published in the Federal Register on 

June 18, 2010 (75 FR 34661). That 

NPRM proposed to require installing 

fuel level float and pressure switch inline fuses on the wing forward spars and 

forward and aft auxiliary fuel tanks, 

depending on the airplane 

configuration. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comment 

received on the proposal and the FAA’s 

response. 

Request To Clarify Applicability 

American Airlines (American) 

requested that we clarify the 

applicability of the NPRM. That NPRM 

identified airplanes in the effectivity of 

Boeing Service Bulletin MD80–28–226, 

dated April 14, 2010, which specifies 

that airplanes are not affected unless the 

actions specified in McDonnell Douglas 

MD–80 Service Bulletin 28–054 or 28– 

058 have been done or the float switches 

have been installed. (These service 

bulletins are currently at Revision 1, 

dated April 15, 1992; and Revision 2, 

dated July 6, 1992; respectively.) 

American reports that it operates 

airplanes with switches incorporated in 

production, but not installed 

specifically in accordance with 

McDonnell Douglas MD–80 Service 

Bulletin 28–054 or 28–058. American 

therefore requests that we clarify the 

applicability of the proposed AD to 

specify whether airplanes equipped 

with the subject fuel float/pressure 

switches—regardless of the method of 

installation—are affected. 

We agree to provide clarification. 

McDonnell Douglas MD–80 Service 

Bulletins 28–054 and 28–058 specify 

that the switches are installed in 

production on specified and subsequent 

fuselage numbers. If switches are 

installed using McDonnell Douglas 

Service Bulletin 28–054 or 28–058 or 

production equivalent, the actions of 

this AD are required. We have added 

Note 1 in this AD to clarify the 

applicability. 

Change to the Installation 

Requirements 

The NPRM referred to Boeing Service 

Bulletin MD80–28–226, dated April 14, 

2010, as the appropriate source of 

service information for the proposed 

requirements. Boeing has identified 

errors in certain references identified in 

that service bulletin, and issued Service 

Bulletin Information Notice MD80–28– 

226 IN 01, dated April 23, 2010, to 

correct these errors. We have included 

these corrections in new paragraph (h) 

in this final rule. 

Explanation of Change Made to the 

[Proposed] AD 

We have revised this AD to identify 

the legal name of the manufacturer as 

published in the most recent type 

certificate data sheet for the affected 

airplane models. 

Conclusion 

We reviewed the relevant data, 

considered the comment received, and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously. 

We determined that these changes will 

not increase the economic burden on 

any operator or increase the scope of the 

AD. 

Costs of Compliance 

We estimate that this AD affects 640 

airplanes of U.S. registry. The following 

table provides the estimated costs, 

depending on the airplane 

configuration, for U.S. operators to 

comply with this AD. 

ESTIMATED COSTS

Action Work hours Average labor rate 

per hour Parts Cost per product 

Number of U.S.- 

registered 

airplanes 

Fleet cost 

Installation .......... Between 7 and 

17.

$85 Between $817 

and $1,725.

Between $1,412 

and $3,170.

640 Between 

$903,680 and 

$2,028,800. 

mstockstill on DSKH9S0YB1PROD with RULES

Federal Register / Vol. 76, No. 8 / Wednesday, January 12, 2011 / Rules and Regulations 1995 

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, 

(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): 

2011–01–16 The Boeing Company: 

Amendment 39–16573; Docket No. 

FAA–2010–0549; Directorate Identifier 

2010–NM–109–AD. 

Effective Date 

(a) This AD is effective February 16, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to The Boeing 

Company Model DC–9–81 (MD–81), DC–9– 

82 (MD–82), DC–9–83 (MD–83), DC–9–87 

(MD–87), and MD–88 airplanes; certificated 

in any category; as identified in Boeing 

Service Bulletin MD80–28–226, dated April 

14, 2010. 

Note 1: The applicability of this AD is 

limited to airplanes on which switches are 

installed in accordance with McDonnell 

Douglas MD–80 Service Bulletin 28–054, 

dated April 8, 1991, or Revision 1, dated 

April 15, 1992; or McDonnell Douglas MD– 

80 Service Bulletin 28–058, dated April 8, 

1991, Revision 1, dated August 2, 1991, or 

Revision 2, dated July 6, 1992; or production 

equivalent. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 28: Fuel. 

Unsafe Condition 

(e) This AD results from fuel system 

reviews conducted by the manufacturer. The 

Federal Aviation Administration is issuing 

this AD to prevent the potential of ignition 

sources inside fuel tanks, which, in 

combination with flammable fuel vapors, 

could result in fuel tank explosions and 

consequent loss of the airplane. 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Fuse Installation 

(g) Within 60 months after the effective 

date of this AD, install fuel level float and 

pressure switch in-line fuses, and do 

applicable wiring changes, in the applicable 

locations specified in paragraph (g)(1), (g)(2), 

or (g)(3) of this AD. Do the actions in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 

MD80–28–226, dated April 14, 2010, except 

as required by paragraph (h) of this AD. 

(1) For Groups 1 through 6: On the left, 

right, and center wing forward spars. 

(2) For Groups 7 and 8: On the left, right, 

and center wing forward spars, and aft 

auxiliary fuel tank. 

(3) For Groups 9 through 11: On the left, 

right, and center wing forward spars, forward 

auxiliary fuel tank, and aft auxiliary fuel 

tank. 

Exception to Service Bulletin Specifications 

(h) Paragraph 3.B.1. of Boeing Service 

Bulletin MD80–28–226, dated April 14, 2010, 

for Groups 1 through 11, refers to the Boeing 

MD80 Airplane Maintenance Manual (AMM) 

defueling procedure MD80 AMM 12–13–00. 

The correct reference is Boeing MD80 AMM 

12–11–01. 

Alternative Methods of Compliance 

(AMOCs) 

(i)(1) The Manager, Los Angeles Aircraft 

Certification Office (ACO), 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: Samuel 

Lee, Aerospace Engineer, Propulsion Branch, 

ANM–140L, FAA, Los Angeles ACO, 3960 

Paramount Boulevard, Lakewood, California 

90712–4137; telephone 562–627–5262; fax 

562–627–5210. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your principal maintenance inspector 

(PMI) or principal avionics inspector (PAI), 

as appropriate, or lacking a principal 

inspector, your local Flight Standards District 

Office. The AMOC approval letter must 

specifically reference this AD. 

Related Information 

(j) For more information about this AD, 

contact Samuel Lee, Aerospace Engineer, 

Propulsion Branch, ANM–140L, FAA, Los 

Angeles ACO, 3960 Paramount Boulevard, 

Lakewood, California 90712–4137; telephone 

562–627–5262; fax 562–627–5210; e-mail 

samuel.lee@faa.gov. 

Material Incorporated by Reference 

(k) You must use Boeing Service Bulletin 

MD80–28–226, dated April 14, 2010, to do 

the actions required by this AD, unless the 

AD specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, 3855 Lakewood Boulevard, MC 

D800–0019, Long Beach, California 90846– 

0001; telephone 206–544–5000, extension 2; 

fax 206–766–5683; e-mail 

dse.boecom@boeing.com; Internet https:// 

www.myboeingfleet.com. 

(3) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

(4) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at an NARA facility, call 202–741– 

6030, or go to http://www.archives.gov/

federal_register/code_of_federal_regulations/

ibr_locations.html. 

mstockstill on DSKH9S0YB1PROD with RULES

1996 Federal Register / Vol. 76, No. 8 / Wednesday, January 12, 2011 / Rules and Regulations 

Issued in Renton, Washington, on 

December 27, 2010. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–33345 Filed 1–11–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0014; Directorate 

Identifier 2010–CE–066–AD; Amendment 

39–16577; AD 2011–02–04] 

RIN 2120–AA64 

Airworthiness Directives; M7 

Aerospace LP (Type Certificate 

Previously Held by Fairchild Aircraft 

Incorporated) Models SA26–AT, SA26– 

T, 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), and 

SA227–TT Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD requires 

repetitively inspecting the cockpit 

heated windshields for damage and 

replacing damaged windshields. This 

AD was prompted by reports from the 

windshield manufacturer of inner glass 

ply fracture. We are issuing this AD to 

detect and correct damage to the cockpit 

heated windshield, which could result 

in failure of the windshield with 

consequent rapid cabin decompression 

and loss of control of the airplane. 

DATES: This AD is effective January 24, 

2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publication listed in the AD 

as of January 24, 2011. 

We must receive comments on this 

AD by February 28, 2011. 

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 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

For service information identified in 

this AD, contact M7 Aerospace LP, 

10823 NE Entrance Road, San Antonio, 

Texas 78216; telephone: (210) 824– 

9421; Internet: http:// 

www.m7aerospace.com. You may 

review copies of the referenced service 

information at the FAA, Small Airplane 

Directorate, 901 Locust St., Kansas City, 

Missouri 64016. 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; 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 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: 

Hung Nguyen, Aerospace Engineer, Fort 

Worth Airplane Certification Office, 

FAA, 2601 Meacham Blvd., Fort Worth, 

Texas 76137–0150; phone: (817) 222– 

5155; fax: (817) 222–5960; e-mail: 

hung.v.nguyen@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We received reports from the 

windshield manufacturer of inner glass 

ply fractures found on 19 windshields 

over a 32-month period. As a result of 

the fractures, a windshield on one of the 

affected airplanes was reported to have 

failed completely. 

This condition, if not corrected, could 

result in failure of the cockpit heated 

windshield, causing rapid cabin 

decompression and loss of control of the 

airplane. 

Relevant Service Information 

We reviewed M7 Aerospace Service 

Bulletins 26–56–001, 226–56–011, 227– 

56–012, and CC7–56–009, all dated 

December 1, 2010. These service 

bulletins describe procedures for 

repetitively inspecting the cockpit 

heated windshield for damage and 

replacing damaged windshields. 

FAA’s Determination 

We are issuing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

AD Requirements 

This AD requires accomplishing the 

actions specified in the service 

information described previously, 

except as discussed under ‘‘Differences 

Between the AD and the Service 

Information.’’ 

Interim Action 

We consider this AD interim action. 

The design approval holder is currently 

developing a modification that will 

address the unsafe condition identified 

in this AD. Once this modification is 

developed, approved, and available, we 

might consider additional rulemaking. 

FAA’s Justification and Determination 

of the Effective Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD. The FAA has found that the risk to 

the flying public justifies waiving notice 

and comment prior to adoption of this 

rule because this condition could result 

in failure of the cockpit windshield. 

This failure could lead to rapid cabin 

decompression and loss of control of the 

airplane. Therefore, we find that notice 

and opportunity for prior public 

comment are impracticable and that 

good cause exists for making this 

amendment effective in less than 30 

days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety and 

was not preceded by notice and an 

opportunity for public comment. 

However, we invite you to send any 

written data, views, or arguments about 

this AD. Send your comments to an 

address listed under the ADDRESSES

section. Include the docket number 

FAA–2011–0014 and Directorate 

Identifier 2010–CE–066–AD at the 

beginning of your comments. We 

specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this 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 AD. 

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