25264 Federal Register / Vol. 76, No. 86 / Wednesday, May 4, 2011 / Proposed Rules 

AOT specified in Table 1 of this AD. The 

report must include the inspection results, a 

description of any discrepancies found, the 

airplane serial number, and the number of 

landings and flight hours on the airplane. 

(1) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 30 days after the inspection. 

(2) If the inspection was done before the 

effective date of this AD: Submit the report 

within 30 days after the effective date of this 

AD. 

Parts Installation 

(k) As of the effective date of this AD, no 

person may install, on any airplane, a RAT 

turbine lower gear box assembly, as 

identified by part number in the applicable 

Hamilton Sundstrand service bulletin 

specified in Table 2 of this AD, unless it has 

been inspected and all applicable corrective 

actions have been done, in accordance with 

the requirements of this AD. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(l) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, 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 International Branch, send it to ATTN: 

Dan Rodina, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue, SW., Renton, Washington 98057– 

3356; telephone (425) 227–2125; fax (425) 

227–1149. 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 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: 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, 

and 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 

(m) Refer to the applicable MCAI European 

Aviation Safety Agency (EASA) AD specified 

in Table 4 of this AD, the Airbus AOTs 

specified in Table 1 of this AD, and the 

Hamilton Sundstrand service bulletins 

specified in Table 2 of this AD, for related 

information. 

TABLE 4—EASA ADS

For model— EASA AD— Dated— 

A300–600 and A310 series airplanes .......................................................................... 2009–0258 December 10, 2009. 

A318, A319, A320, and A321 series airplanes ............................................................ 2010–0120 June 21, 2010.

A330 and A340 series airplanes .................................................................................. 2009–0260 December 10, 2009 (corrected December 

14, 2009). 

Issued in Renton, Washington, on April 26, 

2011. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–10816 Filed 5–3–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0450; Directorate 

Identifier 2011–CE–010–AD] 

RIN 2120–AA64 

Airworthiness Directives; Cessna 

Aircraft Company (Cessna) Models 

337, 337A (USAF 02B), 337B, 337C, 

337D, 337E, T337E, 337F, T337F, 337G, 

T337G, M337B, F 337E, FT337E, F 

337F, FT337F, F 337G, and FT337GP 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above. This proposed 

AD would require inspecting the wings 

for internal and external damage, 

repairing any damage, reinforcing the 

wings, installing operational limitation 

placards in the cockpit, and adding 

limitations to the airplane flight manual 

supplement. This proposed AD was 

prompted by a review of installed Flint 

Aero, Inc. wing tip auxiliary fuel tanks, 

Supplemental Type Certificate (STC) 

SA5090NM. We are issuing this 

proposed AD to detect and correct 

damage in the wings and to prevent 

overload failure of the wing due to the 

installation of the STC. Damage in the 

wing or overload failure of the wing 

could result in structural failure of the 

wing, which could result in loss of 

control. 

DATES: We must receive comments on 

this proposed AD by June 20, 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: 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 Flint Aero, 

Inc., 1942 Joe Crosson Drive, El Cajon, 

CA 92020; phone: (619) 448–1551; fax: 

(619) 448–1571; Internet: http:// 

www.flintaero.com. You may review 

copies of the referenced service 

information at the FAA, Small Airplane 

Directorate, 901 Locust, Kansas City, 

MO 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:// 


srobinson on DSKHWCL6B1PROD with PROPOSALS
Federal Register / Vol. 76, No. 86 / Wednesday, May 4, 2011 / Proposed Rules 25265 

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 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: Dara 

Albouyeh, Aerospace Engineer, FAA, 

Los Angeles Aircraft Certification 

Office, 3960 Paramount Blvd., 

Lakewood, CA 90712; phone: (562) 627– 

5222; fax: (562) 627–5210; e-mail: 

dara.albouyeh@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– 

2011–0450; Directorate Identifier 2011– 

CE–010–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 

In May 2010, we reviewed wing tip 

auxiliary fuel tank extension STCs to 

Cessna 336 and 337 series airplanes for 

compliance with airworthiness 

standards. Due to the STC similarities 

between Aviation Enterprises wing tip 

auxiliary fuel tank extensions and Flint 

Aero, Inc. wing tip auxiliary fuel tank 

extensions, both were reviewed for 

possible wing overload conditions. 

In June 2010, we determined the 

proper design loads for both Aviation 

Enterprises wing tip auxiliary fuel tank 

extension and Flint Aero, Inc. wing tip 

auxiliary fuel tank extension STCs 

exceeded the strength capabilities of the 

outer portions of the wing. 

On October 4, 2010, we issued AD 

2010–21–18, Amendment 39–16478 (75 

FR 64111, October 19, 2010), which 

applies to Cessna Models 336, 337, 

337A (USAF 02B), 337B, M337B (USAF 

02A), T337B, 337C, T337C, 337D, 

T337D, 337E, T337E, 337F, T337F, 

337G, T337G, 337H, P337H, T337H, 

T337H–SP, F337E, FT337E, F337F, 

FT337F, F337G, FT337GP, F337H, and 

FT337HP airplanes that are now or have 

ever been modified by Aviation 

Enterprises wing tip auxiliary fuel tank 

extensions Supplemental Type 

Certificates (STC) SA02055AT, 

SA02056AT, SA02307AT, or 

SA02308AT. 

In January 2011, Flint Aero, Inc. 

confirmed the under-strength condition 

of the outer wing section. 

This condition, if not corrected, could 

result in structural failure of the wing, 

which could result in loss of control. 

Relevant Service Information 

We reviewed Flint Aero, Inc. Service 

Bulletin FA2, Rev 2, dated April 8, 

2011, and Flint Aero, Inc. Drawing FA2, 

Rev A, dated April 8, 2011. The service 

information describes procedures for the 

reinforcement of the upper wing skin, 

the wing front spar cap, and the 

stringers. 

FAA’s Determination 

We are proposing 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. 

Proposed AD Requirements 

This proposed AD would require 

inspecting the wings for internal and 

external damage, repairing any damage, 

reinforcing the wings, installing 

operational limitation placards in the 

cockpit, and adding limitations to the 

Flint Aero, Inc. Airplane Flight Manual 

Supplement. 

Costs of Compliance 

We estimate that this AD affects 33 

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 

Inspection of the wing for damage ................ 5 work-hours × $85 per hour = 

$425 per inspection cycle.

Not applicable ..... $425 per inspection cycle.$14,025 per inspection cycle. 

Fabricating and installing placards in the 

cockpit.

1 work-hour × $85 per hour = $85 .. Not applicable ..... $85 ...................... $2,805. 

Modifying the Limitations section of the Flint 

Aero, Inc. Airplane Flight Manual Supplement.

.5 work-hour × $85 per hour = 

$42.50.

Not applicable ..... $42.50 ................. $1,402.50. 

Reinforcing the upper wing skin, stringer, 

and wing front spar cap.

25 work-hours × $85 per hour = 

$2,125.

$1,070 ................. $3,195 ................. $105,435. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. Subtitle VII: 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in subtitle VII, 

part A, subpart III, section 44701: 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would not have a 

substantial direct effect on the States, on 

the relationship between the national 

Government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 


srobinson on DSKHWCL6B1PROD with PROPOSALS
25266 Federal Register / Vol. 76, No. 86 / Wednesday, May 4, 2011 / Proposed Rules 

For the reasons discussed above, I 

certify this proposed regulation: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

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

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

Cessna Aircraft Company: Docket No. FAA– 

2011–0450; Directorate Identifier 2011– 

CE–010–AD. 

Comments Due Date 

(a) We must receive comments by June 20, 

2011. 

Affected ADs 

(b) AD 2010–21–18, Amendment 39– 

16478, is related to the subject of this AD. 

Applicability 

(c) This AD applies to Cessna Aircraft 

Company (Cessna) Models 337, 337A (USAF 

02B), 337B, 337C, 337D, 337E, T337E, 337F, 

T337F, 337G, T337G, M337B, F 337E, 

FT337E, F 337F, FT337F, F 337G, and 

FT337GP airplanes, all serial numbers, that: 

(1) Are certificated in any category; and 

(2) Are or have ever been modified by Flint 

Aero, Inc. Supplemental Type Certificate 

(STC) SA5090NM. 

Subject 

(d) Joint Aircraft System Component 

(JASC)/Air Transport Association (ATA) of 

America Code 57; Wings. 

Unsafe Condition 

(e) This AD was prompted by a review of 

installed Flint Aero, Inc. wing tip auxiliary 

fuel tanks, STC SA5090NM. We are issuing 

this AD to detect and correct damage in the 

wings and to prevent overload failure of the 

wing due to the installation of the STC. 

Damage in the wing or overload failure of the 

wing could result in structural failure of the 

wing, which could result in loss of control. 

Compliance 

(f) Comply with this AD within the 

compliance times specified, unless already 

done. 

Required Actions 

(g) Within the next 50 hours time-inservice (TIS) after the effective date of this 

AD or within 30 days after the effective date 

of this AD, whichever occurs first, do a 

general and focused inspection of the left and 

right wing for internal and external damage 

at wing stations (WSTA) 150 and 177. Do the 

inspections following Appendix 1 of this AD. 

(h) After the inspection required in 

paragraph (g) of this AD if no damage was 

found and before the modification required 

in paragraph (k) of this AD is incorporated, 

anytime severe and/or extreme turbulence is 

encountered during flight, before the next 

flight do a focused inspection of the wing for 

damage following steps 1, 2, 3, 4, 7, and 10 

in Appendix 1 of this AD. Also inspect for 

signs of distress in the upper front spar in the 

area around WSTA 150 and 177. The 

definition of severe and extreme turbulence 

can be found in table 7–1–9 of the FAA 

Aeronautical Information Manual (AIM). You 

may obtain a copy of the FAA AIM at 

http://www.faa.gov/air_traffic/publications/ 

atpubs/aim/. 

(i) For airplanes that have not had the 

modification specified in paragraphs (j) and 

(k) incorporated, within the next 50 hours 

time-in-service (TIS) after the effective date 

of this AD or within 30 days after the 

effective date of this AD, fabricate a placard 

(using at least 1⁄8-inch letters) with the 

following words and install the placard on 

the instrument panel within the pilot’s clear 

view: 

(1) ‘‘MAINTAIN AT LEAST 12 GAL OF 

FUEL IN EACH WING TIP FUEL TANK FOR 

AIRPLANE WEIGHTS BETWEEN 3,400 LBS 

AND 4,330 LBS.’’ 

(2) ‘‘MAINTAIN FULL FUEL IN EACH 

WING TIP FUEL TANK FOR AIRPLANE 

WEIGHTS AT OR ABOVE 4,330 LBS.’’ 

(j) If damage or signs of distress are found 

during the inspections required in 

paragraphs (g) and (h) of this AD, before 

further flight do the following: 

(1) Repair all damaged and distressed parts 

following FAA Advisory Circular (AC) 

43.13–1B, Chapter 4, which can be found at 

http://rgl.faa.gov/; 

(2) Incorporate the modification 

reinforcement specified in Flint Aero, Inc. 

Service Bulletin FA2, Rev 2, dated April 8, 

2011, following Flint Aero, Inc. Drawing 

FA2, Rev A, dated April 8, 2011; 

(3) Remove the placard specified in 

paragraph (i) of this AD; 

(4) Fabricate a new placard (using at least 1⁄8-inch letters) with the following words and 

install the placard on the instrument panel 

within the pilot’s clear view: ‘‘MAINTAIN AT 

LEAST 12 GAL OF FUEL IN EACH WING 

TIP FUEL TANK FOR AIRPLANE WEIGHTS 

AT OR ABOVE 4,330 LBS’’; and 

(5) Incorporate the information from 

Appendix 2 of this AD into the Limitations 

section of the Flint Aero, Inc. Airplane Flight 

Manual Supplement. 

(k) If no damage or signs of distress are 

found during the inspections required in 

paragraphs (g) and (h) of this AD, within the 

next 100 hours TIS after the effective date of 

this AD or within 12 months after the 

effective date of this AD, whichever occurs 

first, do the following: 

(1) Incorporate the modification 

reinforcement specified in Flint Aero, Inc. 

Service Bulletin FA2, Rev 2, dated April 8, 

2011, following Flint Aero, Inc. Drawing 

FA2, Rev A, dated April 8, 2011; 

(2) Remove the placard specified in 

paragraph (i) of this AD; 

(3) Fabricate a new placard (using at least 1⁄8-inch letters) with the following words and 

install the placard on the instrument panel 

within the pilot’s clear view: ‘‘MAINTAIN AT 

LEAST 12 GAL OF FUEL IN EACH WING 

TIP FUEL TANK FOR AIRPLANE WEIGHTS 

AT OR ABOVE 4,330 LBS’’; and 

(4) Incorporate the information from 

Appendix 2 of this AD into the Limitations 

section of the Flint Aero, Inc. Airplane Flight 

Manual Supplement. 

(l) You may incorporate the modification 

reinforcement specified in Flint Aero, Inc. 

Service Bulletin FA2, Rev 2, dated April 8, 

2011, following Flint Aero, Inc. Drawing 

FA2, Rev A, dated April 8, 2011, at any time 

after the inspection required in paragraph (g) 

of this AD but no later than the compliance 

time specified in paragraph (k) of this AD as 

long as no cracks were found. As required in 

paragraph (j) of this AD, the modification 

reinforcement must be incorporated before 

further flight if damage or signs of distress 

are found. 

Alternative Methods of Compliance 

(AMOCs) 

(m)(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. 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. 

Related Information 

(n) For more information about this AD, 

contact Dara Albouyeh, Aerospace Engineer, 

FAA, Los Angeles ACO, 3960 Paramount 

Blvd., Lakewood, CA 90712; phone: (562) 

627–5222; fax: (562) 627–5210; e-mail: 

dara.albouyeh@faa.gov. 

(o) For service information identified in 

this AD, contact Flint Aero, Inc., 1942 Joe 

Crosson Drive, El Cajon, CA 92020; phone: 

(619) 448–1551; fax: (619) 448–1571; 

Internet: http://www.flintaero.com. You may 

review copies of the referenced service 

information at the FAA, Small Airplane 

Directorate, 901 Locust, Kansas City, MO 

64106. For information on the availability of 

this material at the FAA, call (816) 329–4148. 


srobinson on DSKHWCL6B1PROD with PROPOSALS
Federal Register / Vol. 76, No. 86 / Wednesday, May 4, 2011 / Proposed Rules 25267 

Appendix 1 to Docket No. FAA–2011–0450 

General and Focused Inspection Procedures 

Perform a general and focused inspection 

of the wing for internal and external damage 

from wing station (WSTA) 23 to the wing tip. 

The general inspection must be performed in 

accordance with 14 CFR 43.15(c), using a 

checklist that includes at least the scope and 

detail of the items contained in Appendix D 

of 14 CFR part 43. The focused inspection 

must include the items listed below. Remove 

all wing access panels to conduct the 

inspections. Do these inspections following 

the manufacturer’s service information and 

any other appropriate guidance, such as FAA 

Advisory Circular (AC) 43.13–1B Acceptable 

Methods, Techniques, and Practices— 

Aircraft Inspection and Repair. AC 43.13–1B 

can be found at http://rgl.faa.gov/. 

Focused inspection items to look for: 

(1) Wrinkles in upper wing skins, from the 

outboard edge on the fuel tank access covers 

(WSTA 150 or 177) to the WSTA 222 (See 

View B, Figure 3). 

(2) Wrinkles in the upper wing skins from 

WSTA 55 to 66, adjacent to the booms (See 

View E, Figure 6). 

(3) Cracking of the upper wing skins. Pay 

particular attention to any wrinkles, the 

radius between stiffeners at WSTA 150 

(under fuel tank covers), and unreinforced 

access holes (See View B, Figure 3). 

(4) Working (smoking) rivets outboard of 

the wing tank access covers. 

(5) Fasteners with less than two diameters 

edge distance. 

(6) Fasteners with less than four diameters 

center to center spacing. 

(7) Looseness of attachments of the tip 

extension to the wing and wing tip to wing 

extension when pushing up and down on the 

tip. 

(8) Any signs of distress along both front 

and rear spars, particularly in the area 

around WSTA 177. 

(9) Inspect under any repairs to the upper 

skins, particularly in the area just outboard 

of the fuel tank access covers as these may 

be covering up existing damage. 

(10) Inter-rivet buckling of the stringers 

attached to the upper surface skin, outboard 

of the fuel tank access covers (See View F, 

Figure 7). 

(11) Inspect rib at WSTA 222 for damage. 

Trimming of the rib may have been done to 

allow installation of fuel lines (See View A, 

Figure 2). Repair in accordance with AC 

43.13–1B, Chapter 4, paragraph 4–58(g) and 

Figure 4–14, or by using another FAAapproved method that restores equivalent 

strength of the wing rib. 

Appendix 1 to Docket No. FAA–2011–0450 

General and Focused Inspection Procedures 

(Continued) 

(12) Inspect and identify screws, installed 

in tapped (threaded) holes in metal 

substructure, used to attach wing tips, stall 

fences, fuel and electrical components, and 

access doors. For tapped holes, remove 

fastener and open up the diameter to provide 

a smooth bore hole, for the smallest oversize 

fastener, using close tolerance holes noted in 

AC 43.13–1B, paragraph 7–39 or other FAAapproved scheme. Maintain minimum 2 x 

fastener diameter edge distance and 4 x 

fastener diameter center to center spacing. 

Select and install new, equivalent strength or 

stronger, fasteners with nuts/collars in 

accordance with AC 43.13–1B, Chapter 7 and 

AC 43.13–2B, paragraph 108 or other FAAapproved repair. New fasteners must not 

have threads in bearing against the sides of 

the holes. 

(13) Inspect wing skins for unreinforced 

cutouts. (See View C, Figure 4). 

(14) Inspect the upper spar cap horizontal 

flanges for open holes (See View D, Figure 5). 

Appendix 1 to Docket No. FAA–2011–0450 

(Continued) 

BILLING CODE 4910–13–P 


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BILLING CODE 4910–13–C Appendix 1 to Docket No. FAA–2011–0450 

(Continued) 


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BILLING CODE 4910–13–C Appendix 1 to Docket No. FAA–2011–0450 

(Continued) 


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25270 Federal Register / Vol. 76, No. 86 / Wednesday, May 4, 2011 / Proposed Rules 

BILLING CODE 4910–13–C Appendix 1 to Docket No. FAA–2011–0450 

(Continued) 


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BILLING CODE 4910–13–C Appendix 1 to Docket No. FAA–2011–0450 

(Continued) 


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25272 Federal Register / Vol. 76, No. 86 / Wednesday, May 4, 2011 / Proposed Rules 

BILLING CODE 4910–13–C Appendix 1 to Docket No. FAA–2011–0450 

(Continued) 


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Federal Register / Vol. 76, No. 86 / Wednesday, May 4, 2011 / Proposed Rules 25273 

BILLING CODE 4910–13–C 

Appendix 2 to Docket No. FAA–2011–0450 

Airworthiness Limitations for the Flint 

Aero, Inc. Airplane Flight Manual 

Supplement 

‘‘MAINTAIN AT LEAST 12 GAL OF FUEL 

IN EACH WING TIP FUEL TANK FOR 

AIRPLANE WEIGHTS AT OR ABOVE 4,330 

LBS.’’ 

Issued in Kansas City, Missouri, on April 

27, 2011. 

John Colomy, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–10818 Filed 5–3–11; 8:45 am] 

BILLING CODE 4910–13–P 

SECURITIES AND EXCHANGE 

COMMISSION 

17 CFR Parts 229 and 240 

[Release Nos. 33–9203; 34–64366; File No. 

S7–13–11] 

RIN 3235–AK95 

Listing Standards for Compensation 

Committees 

AGENCY: Securities and Exchange 

Commission. 

ACTION: Proposed rule; extension of 

comment period. 

SUMMARY: The Securities and Exchange 

Commission is extending the comment 

period for a release proposing a new 

rule and rule amendments to implement 

the provisions of Section 952 of the 

Dodd-Frank Wall Street Reform and 

Consumer Protection Act of 2010, which 

added Section 10C to the Securities 

Exchange Act of 1934 (the ‘‘Exchange 

Act’’). [Release No. 33–9199; 76 FR 

18966 (April 6, 2011)]. The original 

comment period for Release 33–9199 is 

scheduled to end on April 29, 2011. The 

Commission is extending the time 

period in which to provide the 

Commission with comments on that 

release to May 19, 2011. This action will 

allow interested persons additional time 

to analyze the issues and prepare their 

comments. 

DATES: Comments should be received on 

or before May 19, 2011. 

ADDRESSES: Comments may be 

submitted by any of the following 

methods: 

Electronic Comments 

• Use the Commission’s Internet 

comment form (http://www.sec.gov/ 

rules/proposed.shtml); • Send an e-mail to rulecomments@sec.gov; or • Use the Federal Rulemaking ePortal 

(http://www.regulations.gov). Follow the 

instructions for submitting comments. 

Paper Comments 

• Send paper comments in triplicate 

to Elizabeth M. Murphy, Secretary, U.S. 

Securities and Exchange Commission, 

100 F Street, NE., Washington, DC 

20549–1090. 

All submissions should refer to File 

Number S7–13–11. This file number 

should be included on the subject line 

if e-mail is used. To help us process and 

review your comments more efficiently, 

please use only one method. The 

Commission will post all comments on 

the Commission’s Internet Web site 

(http://www.sec.gov/rules/ 

proposed.shtml). Comments are also 

available for Web site viewing and 

printing in the Commission’s Public 

Reference Room, 100 F Street, NE., 

Washington, DC 20549, on official 

business days between the hours of 


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