Federal Register / Vol. 77, No. 168 / Wednesday, August 29, 2012 / Rules and Regulations 52205 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the following new 

Goodyear Aviation Tires (retreads are not 

affected by this AD), installed on various 

transport category airplanes, including but 

not limited to Bombardier, Inc. Model CL– 

600–2B19 airplanes: 

(1) New tire part number (P/N) 299K63–1 

with the following specifications: 

(i) Tire size: H29x9.0–15; 

(ii) Ply rating: 16PR; and 

(iii) Speed rating: 210 miles per hour. 

(2) Serial numbers (S/N) 01867xxx through 

02737xxx with the following specifications: 

(i) The 5th digit of the serial number must 

be a ‘‘7’’; and 

(ii) ‘‘XXX’’ can be any combination of three 

single digit numbers. 

(d) Subject 

Air Transport Association of America 

(ATA) Code 32: Landing gear. 

(e) Reason 

This AD was prompted by mandatory 

continuing airworthiness information (MCAI) 

issued by the aviation authority of another 

country to identify and correct an unsafe 

condition on an aviation product. The MCAI 

describes the unsafe condition as tire tread 

separations and tread-area bulges on the 

main landing gear tires due to low adhesion 

in the tread should area. We are issuing this 

AD to prevent failure of the main landing 

gear tires during takeoff or landing, which 

could cause damage to the airplane structure, 

flaps, engine, and wheel well and result in 

reduced controllability of the airplane. 

(f) Actions and Compliance 

Unless already done, do the following 

actions in accordance with Goodyear 

Aviation Service Bulletin 2012–32–001, 

dated April 19, 2012. 

(1) Within the next 5 flight cycles 

(landings) after September 13, 2012 (the 

effective date of this AD), inspect the main 

landing gear tires, P/N 299K63–1, to 

determine if an affected S/N tire, as specified 

in paragraph (c) of this AD, is installed. A 

review of the airplane maintenance records is 

acceptable in lieu of this inspection if the P/ 

N and S/N of the tires installed can be 

positively determined from that review. 

Operators that do not maintain landing 

records can determine the number of 

landings by dividing the number of airplane 

hours time-in-service (TIS) by two. 

(2) Before further flight after the inspection 

required in paragraph (f)(1) of this AD, 

replace any tire that has an affected serial 

number. 

(3) As of September 13, 2012 (the effective 

date of this AD), do not install any main 

landing gear tire, P/N 299K63–1, that has an 

affected serial number specified in paragraph 

(c)(2) of this AD. 

(g) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Atlanta 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 Belete, Aerospace Engineer, FAA, 

Atlanta ACO, 1701 Columbia Avenue, 

College Park, Georgia 30337; phone: (404) 

474–5580; fax: (404) 474–5606; email: 

samuel.belete@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. 

(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. 

(h) Special Flight Permit 

We are allowing a one-time special flight 

permit to return the airplane to a suitable 

maintenance base provided a detailed 

inspection of the main landing gear tires is 

done and no tread separation or bulge is 

detected. 

(i) Related Information 

Refer to MCAI Ageˆncia Nacional de 

Aviac ̧a ̃o Civil (ANAC) Brazilian 

Airworthiness Directive 2012–05–01, dated 

June 5, 2012, and Goodyear Aviation Service 

Bulletin 2012–32–001, dated April 19, 2012, 

for related information. 

(j) 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) Goodyear Aviation Service Bulletin 

2012–32–001, dated April 19, 2012. 

(ii) Reserved. 

(3) For Goodyear Aviation Tires service 

information identified in this AD, contact 

Goodyear Aviation, ATTN: Richard 

McKenna—Product Support Manager (North 

America), 100 Business Center Drive, 

Stockbridge, GA 30281; phone: (678) 364– 

8956; fax: (678) 284–6101; email: 

rich_mckenna@goodyear.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/ 

index.html. 

Issued in Kansas City, Missouri, on August 

16, 2012. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2012–20696 Filed 8–28–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0360; Directorate 

Identifier 2010–CE–061–AD; Amendment 

39–17023; AD 2012–08–06] 

RIN 2120–AA64 

Airworthiness Directives; Univair 

Aircraft Corporation Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

certain Univair Aircraft Corporation 

Models (ERCO) 415–C, 415–CD, 415–D, 

E, G; (Forney) F–1 and F–1A; (Alon) A– 

2 and A2–A; and (Mooney) M10 

airplanes. That AD currently requires an 

inspection of the aileron balance 

assembly and ailerons for cracks and 

excessive looseness of associated parts 

with the required repair or replacement 

of defective parts as necessary. This new 

AD would add airplanes to the 

Applicability section; require 

inspections of the ailerons, aileron 

balance assembly, and aileron rigging 

for looseness or wear, require repair or 

replacement of parts as necessary; and 

require a report of the inspection 

results. This new AD was prompted by 

a report of a Univair Aircraft 

Corporation Model ERCO 415–D 

Ercoupe that crashed after an in-flight 

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52206 Federal Register / Vol. 77, No. 168 / Wednesday, August 29, 2012 / Rules and Regulations 

breakup due to possible aileron flutter. 

We are issuing this AD to correct the 

unsafe condition on these products. 

DATES: This AD is effective October 3, 

2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of October 3, 2012. 

ADDRESSES: For service information 

identified in this AD, contact Univair 

Aircraft Corporation, 2500 Himalaya 

Road, Aurora, Colorado 80011; 

telephone: (303) 375–8882, fax: (303) 

375–8888; Internet: http:// 

univairparts.com. 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. 

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: 

Roger Caldwell, Aerospace Engineer, 

FAA, Denver Aircraft Certification 

Office, 26805 East 68th Ave., Room 214, 

Denver, Colorado 80249–6361; 

telephone: (303) 342–1086; fax: (303) 

342–1088; email: 

roger.caldwell@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 52–02–02 (21 

FR 9447, December 4, 1956). That AD 

applies to the specified products. The 

NPRM published in the Federal 

Register on April 14, 2011 (76 FR 

20894, April 14, 2011). That NPRM 

proposed to add airplanes to the 

Applicability section; require 

inspections of the ailerons, aileron 

balance assembly, and aileron rigging 

for looseness or wear; repair or 

replacement of parts as necessary; and 

require a report of the inspection 

results. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal (76 FR 20894, 

April 14, 2011) and the FAA’s response 

to each comment. 

Request To Withdraw NPRM or Change 

the Inspection Interval 

William R. Bayne and Hartmut Beil 

stated that the service bulletin and/or 

the manufacturer’s existing 

recommendations, such as lubricating 

control rod ends at 300 hour intervals, 

are adequate, and the existing AD 52– 

02–02 (21 FR 9447, December 4, 1956) 

is sufficient. They stated that the 

number of in-flight breakups do not 

identify a failure of the flight control 

system and do not justify the need for 

AD action. They also stated the 

inspection interval should be 300 hours 

instead of 100 hours to match the 

existing recommendations, and the 

proposed AD puts a financial burden on 

owners with little or no gain for safety. 

We disagree with these comments. 

This AD will add airplanes to the 

Applicability section that were not 

included in AD 52–02–02 (21 FR 9447, 

December 4, 1956). Also, the flight 

control free play limits can vary or be 

out of tolerance for many more reasons 

than not doing the 300-hour lubrication 

requirement. Also, varying field reports 

indicated that the majority of flight 

control systems are not in tolerance. In 

addition, Ercoupe Service Memorandum 

No. 57, Revision A, dated September 1, 

2008, recommends free play inspection 

every 100 hours. 

Request To Allow for Credit for the 

Calibration of the Airspeed Indicator 

Linda Abrams requested we change 

the calibration of the airspeed indicator 

(ASI) requirement, paragraph (g)(8) of 

the proposed AD (76 FR 20894, April 

14, 2011), to allow for ‘‘unless already 

done’’ credit since that applies to the 

other inspection requirements, and it 

would impose a financial burden on 

owners and operators. 

We agree. ‘‘Unless already done’’ 

credit will be applied for the ASI 

calibration requirement in paragraph 

(g)(8) of this AD as all other ‘‘unless 

already done’’ credit is being applied by 

reference to the Compliance section, 

paragraph (f) of this AD. 

Request To Reference Mooney M–10 

Service and Maintenance Manual 

James E. Dyer of Univair requested the 

Mooney M–10 service and maintenance 

requirements be addressed by separate 

applicable service information since the 

Ercoupe Service Memorandum No. 57 

and 35A, both Revisions A, both dated 

September 1, 2008, are not applicable to 

the Mooney M–10. 

We agree. We revised the ‘‘Required 

Actions’’ section paragraph (g) of this 

AD by adding text that requires 

inspecting and taking corrective action 

on the Mooney M–10 flight control 

system per pages 5–1 through 5–4 of the 

Mooney M–10 Service and Maintenance 

Manual, Serial Numbers 690001 through 

690011 and 700001 and on, Revision A, 

dated September 1, 2008. We also added 

Ercoupe Service Memorandum No. 35A, 

Revision A, dated September 1, 2008, to 

the applicable service information, and 

added an area to the reporting 

requirement pertaining to the use of 

Ercoupe Service Memorandum No. 35A, 

Revision A, dated September 1, 2008. 

Request To Reference Ercoupe Service 

Bulletin No. 20 for the Aileron Balance 

Assembly Requirements 

James E. Dyer commented that 

Ercoupe Service Memorandum No. 20, 

Revision A, dated September 1, 2008, is 

only referenced in the one-time 

reporting requirement of the ‘‘Required 

Actions’’ section, paragraph (g) of the 

proposed AD and not referenced as a 

procedural requirement for the 

inspection of ailerons with counter 

weights. 

We agree. We have revised this AD by 

adding Ercoupe Service Memorandum 

No. 20, Revision A, dated September 1, 

2008, as a reference in the ‘‘Required 

Actions’’ section, paragraph (g), of this 

AD pertaining to airplanes with the 

aileron balance assembly (ERCO part 

number (P/N) 415–16009). 

Request To Require the Airspeed 

Indicator Calibration To Be Done at an 

Instrument Repair Facility 

James E. Dyer, Linda T. Abrams, and 

Jack Chmiel commented that the 

calibration test for the ASI should be 

completed by an authorized instrument 

repair facility because Advisory Circular 

AC 23–8B, Appendix 9 contains 

technical requirements that exceed the 

ability of most owner/operators, repair 

stations, or Airframe & Powerplant 

(A&P) mechanics on this class of 

airplane. 

We partially agree. We have revised 

the ‘‘Required Actions’’ section, 

paragraph (g)(8) of this AD to require an 

FAA-authorized instrument repair 

facility to calibrate the ASI if the bench 

test method is used. However we will 

allow an exception for global 

positioning system (GPS) or other 

owner/operator FAA-approved methods 

of calibrating the ASI following the 

instructions in FAA Advisory Circular 

AC 23–8C, Appendix 9, dated 

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Federal Register / Vol. 77, No. 168 / Wednesday, August 29, 2012 / Rules and Regulations 52207 

November 16, 2011. These procedures 

will be repetitively required every 4 

years and any time maintenance affects 

the system integrity. 

Request To Make the Reporting 

Requirement a One-Time Action 

Jack Chmiel, William R. Bayne, and 

an anonymous commenter stated they 

did not think the Inspection Report 

should be submitted after each 

inspection interval. They didn’t feel the 

referenced report was clearly defined in 

the NPRM as a one-time report that is 

only required at the time of initial 

compliance with the AD. 

We agree. We have revised this AD to 

clearly state the reporting requirement is 

a one-time action submitted after the 

initial inspection. 

Request To Update the P/N ‘‘Costs of 

Compliance’’ 

James E. Dyer commented that there 

has been a revision to a P/N listed in the 

‘‘Costs of Compliance’’ section of this 

AD, and we should change the P/N. 

We agree. We revised this AD to 

reflect the aileron hinge and rudder 

hinge P/N from 415–24003 to F24003 in 

the ‘‘Costs of Compliance’’ section. 

Request To Limit the Aileron Free Play 

Vince Hammons and Jack Chmiel 

commented that the aileron free play 

should be limited to 1⁄8 inch to 5⁄16 inch, 

which they believe would be easily 

attainable and would remove any 

confusion on allowable amount of free 

play. 

We do not agree. Ercoupe Service 

Memorandums No. 56 and No. 57, both 

Revisions A, both dated September 1, 

2008, state that 7⁄16 inch is allowable for 

ailerons with counter weights, and 5⁄16

inch is allowable for ailerons without 

counter weights per the original design. 

Anything less could be unattainable due 

to different wear patterns and usage 

between airplane units and the services 

times and duration of the type design 

for the fleet since inception. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (76 FR 

20894, April 14, 2011) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (76 FR 20894, 

April 14, 2011). 

We also 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 2,600 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED RETAINED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Inspect the ailerons for 

cracks in the support 

structure and skin.

4 work-hours × $85 per hour = $340 ........................ Not applicable .................. $340 $884,000 

ESTIMATED NEW COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Remove load from nose 

wheel and adjust rigging.

.5 work-hour × $85 per hour = $42.50 ...................... Not applicable .................. $42.50 $110,500 

We estimate the following costs to do 

any necessary replacements for the 

flight control system that would be 

required based on the results of the 

inspection. We have no way of 

determining the number of airplanes 

that may need this replacement: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Install aileron hinge .. 2 work-hours × $85 per hour = $170 ...... Aileron Hinge Part Number (P/N) F24003 $25 ....................... $195 

Install elevator hinge 2 work-hours × $85 per hour = $170 ...... Elevator Hinge P/N 415–22007 $40 ........................................ 210 

Install elevator hinge 2 work-hours × $85 per hour = $170 ...... Elevator Hinge P/N 415–22008 $83 ........................................ 253 

Install rudder hinge .. 2 work-hours × $85 per hour = $170 ...... Rudder Hinge P/N F24003 $25 ............................................... 195 

Install aileron rodend bearing.2 work-hours × $85 per hour = $170 ...... Aileron Rod-End Bearing P/N GMM–3M–670 $20 ................. 190 

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 

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52208 Federal Register / Vol. 77, No. 168 / Wednesday, August 29, 2012 / Rules and Regulations 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We have determined that this AD will 

not have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

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

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing airworthiness directive (AD) 

52–02–02, (21 FR 9447, December 4, 

1956), and adding the following new 

AD: 

2012–08–06 Univair Aircraft Corporation: 

Amendment 39–17023; Docket No. 

FAA–2011–0360; Directorate Identifier 

2010–CE–061–AD. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective October 3, 2012. 

(b) Affected ADs 

This AD supersedes AD 52–02–02 (21 FR 

9447, December 4, 1956). 

(c) Applicability 

This AD applies to Univair Aircraft 

Corporation Models (ERCO) 415–C, 415–CD, 

415–D, E, G; (Forney) F–1 and F–1A; (Alon) 

A–2 and A2–A; and (Mooney) M10 airplanes, 

all serial numbers, that are certificated in any 

category. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 27, Flight Controls. 

(e) Unsafe Condition 

This AD was prompted by a Univair 

Aircraft Corporation Model ERCO 415–D 

Ercoupe that crashed after an in-flight 

breakup due to possible aileron flutter. We 

are issuing this AD to correct the unsafe 

condition on these products. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

TABLE 1 OF PARAGRAPH (G)—REQUIRED ACTIONS

What must be done? When must it be done? How it must be done 

(1) For all airplanes: Inspect the ailerons for 

cracks in the support structure and skin.

Within the next 25 hours time-in-service (TIS) 

after October 3, 2012 (the effective date of 

this AD) or within 3 months after October 3, 

2012 (the effective date of this AD), whichever occurs first. Repetitively thereafter inspect at intervals not to exceed 100 hours 

TIS or 12 months, whichever occurs first.

For all airplanes except the Mooney M–10, 

follow Ercoupe Service Memorandums No. 

56 and 35A, both Revisions A, both dated 

September 1, 2008. For the Mooney M–10 

follow the Mooney M–10 Service and Maintenance Manual, Serial Numbers 690001 

through 690011 and 700001 and on, Revision A, dated September 1, 2008, Section 

V, pages 5–1 through 5–4. 

(2) For airplanes with the aileron balance assembly (ERCO Part Number (P/N) 415– 

16009) installed: Inspect the assembly for 

cracks in the support structure and skin.

Within the next 25 hours TIS after October 3, 

2012 (the effective date of this AD) or within 3 months after October 3, 2012 (the effective date of this AD), whichever occurs 

first. Repetitively thereafter inspect at intervals not to exceed 100 hours TIS or 12 

months, whichever occurs first.

Follow Ercoupe Service Memorandums No. 

20, 56, and 57, all Revisions A, all dated 

September 1, 2008; and for Models E and 

(Forney) F–1 and F–1A, follow Ercoupe 

Service Memorandum No. 35A, Revision A, 

dated September 1, 2008. 

(3) For all airplanes: If any cracking is found 

during the inspections required in paragraphs 

(g)(1) and/or (g)(2) of this AD, repair or replace cracked parts.

Before further flight after the inspection where 

the cracking was found.

Follow Ercoupe Service Memorandums No. 

20, 56, and 57, all Revisions A, all dated 

September 1, 2008; and for Models E and 

(Forney) F–1 and F–1A, follow Ercoupe 

Service Memorandum No. 35A, Revision A, 

dated September 1, 2008. 

(4) For airplanes with the aileron balance assembly (ERCO P/N 415–16009) installed: Inspect the four No. 6–32 screws that attach 

the balance weight support to the aileron for 

looseness and damage.

Within the next 25 hours TIS after October 3, 

2012 (the effective date of this AD) or within 3 months after October 3, 2012 (the effective date of this AD), whichever occurs 

first. Repetitively thereafter inspect at intervals not to exceed 100 hours TIS or 12 

months, whichever occurs first.

Follow Ercoupe Service Memorandums No. 

20, 56, and 57, all Revisions A, all dated 

September 1, 2008; and for Models E and 

(Forney) F–1 and F–1A, follow Ercoupe 

Service Memorandum No. 35A, Revision A, 

dated September 1, 2008. 

(5) For all airplanes: If any looseness or damage is found during the inspection of the 

screws required in paragraph (g)(4) of this 

AD, replace the screws with AN 526–632 

screws, making sure to not overstress during 

tightening.

Before further flight after the inspection where 

the looseness or damage was found.

Follow Ercoupe Service Memorandums No. 

20, 56, and 57, all Revisions A, all dated 

September 1, 2008; and for Models E and 

(Forney) F–1 and F–1A, follow Ercoupe 

Service Memorandum No. 35A, Revision A, 

dated September 1, 2008. 

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Federal Register / Vol. 77, No. 168 / Wednesday, August 29, 2012 / Rules and Regulations 52209 

TABLE 1 OF PARAGRAPH (G)—REQUIRED ACTIONS—Continued 

What must be done? When must it be done? How it must be done 

(6) For airplanes with the aileron balance assembly (ERCO P/N 415–16009) installed: Inspect the aileron hinges and aileron control 

system for excessive looseness or wear in 

hinge pins or bearings. If, with one aileron 

blocked in the neutral position, the total play 

of the other aileron, measured at the trailing 

edge, exceeds 7⁄16-inch, inspect all the joints 

and bearings and tighten or replace those 

which are loose.

Within the next 25 hours TIS after October 3, 

2012 (the effective date of this AD) or within 3 months after October 3, 2012 (the effective date of this AD), whichever occurs 

first. Repetitively thereafter inspect at intervals not to exceed 100 hours TIS or 12 

months, whichever occurs first.

Follow Ercoupe Service Memorandums No. 

20, 56, and 57, all Revisions A, all dated 

September 1, 2008; and for Models E and 

(Forney) F–1 and F–1A, follow Ercoupe 

Service Memorandum No. 35A, Revision A, 

dated September 1, 2008. 

(7) For airplanes that do not have the aileron 

balance assembly (ERCO P/N 415–16009) 

installed: Inspect the aileron hinges and aileron control system for excessive looseness 

or wear in hinge pins or bearings. If, with one 

aileron blocked in the neutral position the 

total play of the other aileron, measured at 

the trailing edge, exceeds 5⁄16-inch, inspect 

all the joints and bearings and tighten those 

which are loose.

Within the next 25 hours TIS after October 3, 

2012 (the effective date of this AD) or within 3 months after October 3, 2012 (the effective date of this AD), whichever occurs 

first.

Follow Ercoupe Service Memorandums No. 

20, 56, and 57, all Revisions A, all dated 

September 1, 2008; and for Models E and 

(Forney) F–1 and F–1A, follow Ercoupe 

Service Memorandum No. 35A, Revision A, 

dated September 1, 2008. 

(8) For all airplanes: Determine that the airspeed instrument is correctly calibrated and 

distinctly marked in accordance with the operating limitations.

Within the next 25 hours TIS after October 3, 

2012 (the effective date of this AD) or within 3 months after October 3, 2012 (the effective date of this AD), whichever occurs 

first, and repetitively thereafter every four 

years, and any time maintenance occurs 

that affects the system integrity.

For airspeed instrument calibration by bench 

test method, you must use an FAA-authorized instrument repair facility. For airspeed 

calibration by global positioning system 

(GPS) or other owner/operator FAA-approved method, you may follow the instructions in Advisory Circular (AC) AC 23–8C, 

Appendix 9, dated November 16, 2011. AC 

23–8C can be found at: http:// 

www.airweb.faa.gov/Regulatory_and_ Guidance_Library/rgAdvisoryCircular.nsf/0/ 

bc4325ad70e84ff58625795d00635d7c/ 

$FILE/23-8C.pdf. 

(9) For all airplanes except the Mooney M–10: 

Remove load from nose wheel and adjust rigging.

Within the next 25 hours TIS after October 3, 

2012 (the effective date of this AD) or within 3 months after October 3, 2012 (the effective date of this AD), whichever occurs 

first. Repetitively thereafter adjust at intervals not to exceed 100 hours TIS or 12 

months, whichever occurs first.

Follow Ercoupe Service Memorandum No. 35, 

Revised January 6, 2006, and/or Ercoupe 

Service Memorandum 35A, Revision A, 

dated September 1, 2008. 

(10) For all airplanes: Submit a one-time report 

from the initial inspections and/or actions required in paragraphs (g)(1), (g)(2), (g)(4), 

(g)(6), (g)(7), (g)(8), and (g)(9) of this AD.

Within 30 days after the initial inspections 

and/or actions required in paragraphs 

(g)(1), (g)(2), (g)(4), (g)(6), (g)(7), (g)(8), 

and (g)(9) of this AD, or 30 days after October 3, 2012 (the effective date of this AD) if 

you are using the ‘‘unless already done’’ 

credit.

Use the reporting form found in Figure 1 of 

paragraph (g)(10) of this AD and send the 

report to the following offices: Roger A. 

Caldwell, Aerospace Engineer, FAA, ANM– 

100D, Denver Aircraft Certification Office 

(ACO), 26805 East 68th Avenue, Room 

214, Denver, Colorado 80249–6361; and 

Univair Aircraft Corporation, 2500 Himalaya 

Road, Aurora, Colorado 80011. 

BILLING CODE 4910–13–P 

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BILLING CODE 4910–13–C 

(h) 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 


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52212 Federal Register / Vol. 77, No. 168 / Wednesday, August 29, 2012 / Rules and Regulations 

20591, Attn: Information Collection 

Clearance Officer, AES–200. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Denver 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 Principal Maintenance Inspector 

or Principal Avionics Inspector, as 

appropriate, or lacking a principal inspector, 

your local Flight Standards District Office. 

(3) AMOCs approved for AD 52–02–02 (21 

FR 9447, December 4, 1956) are approved as 

AMOCs for this AD. 

(j) Related Information 

For more information about this AD, 

contact Roger Caldwell, Aerospace Engineer, 

FAA, Denver ACO, 26805 East 68th Ave., 

Room 214, Denver, Colorado 80249–6361; 

telephone: (303) 342–1086; fax: (303) 342– 

1088; email: roger.caldwell@faa.gov. 

(k) 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) Ercoupe Service Memorandum No. 56, 

Revision A, dated September 1, 2008; 

(ii) Ercoupe Service Memorandum No. 57, 

Revision A, dated September 1, 2008; 

(iii) Ercoupe Service Memorandum No. 35, 

revised January 6, 2006; 

(iv) Ercoupe Service Memorandum No. 

35A, Revision A, dated September 1, 2008; 

(v) Ercoupe Service Memorandum No. 20, 

Revision A, dated September 1, 2008; and 

(vi) Mooney M–10 Service and 

Maintenance Manual, Serial Numbers 690001 

through 690011 and 700001 and on, Section 

V, pages 5–1 through 5–4, Revision A, dated 

September 1, 2008. 

Note for paragraph (k)(2)(i), (k)(2)(ii), 

(k)(2)(iv), (k)(2)(v), and (k)(2)(vi) of this AD: 

The only change in Revision A of the above 

listed service information was to add dates to 

the previously undated service information. 

(3) For Univair Aircraft Corporation service 

information identified in this AD, contact 

Univair Aircraft Corporation, 2500 Himalaya 

Road, Aurora, Colorado 80011; telephone: 

(303) 375–8882, facsimile: (303) 375–8888; 

Internet: http://univairparts.com. 

(4) You may view this service information 

at FAA, Small Airplane Directorate, 901 

Locust St., Kansas City, MO 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/ 

index.html. 

Issued in Kansas City, Missouri, on August 

16, 2012. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2012–21018 Filed 8–28–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1326; Directorate 

Identifier 2010–NM–177–AD; Amendment 

39–17144; AD 2012–15–15] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

certain The Boeing Company Model 

757–200, –200CB, and –300 series 

airplanes. That AD currently requires 

initial and repetitive inspections of the 

fuselage skin and bear strap at the 

forward, upper corner of the L1 entry 

door cutout for cracking, and repair if 

necessary. That action also provides an 

optional terminating action for the 

repetitive inspections. This new AD 

requires additional inspections for 

airplanes having repairs or preventative 

modifications installed and inspections 

for certain other airplanes. This AD also 

adds airplanes to the applicability. This 

AD was prompted by reports of 

additional cracking in the fuselage skin. 

We are issuing this AD to detect and 

correct cracking of the fuselage skin and 

bear strap at the forward upper corner 

of the L1 entry door cutout, which could 

result in reduced structural integrity of 

the L1 entry door, and consequent rapid 

decompression of the airplane. 

DATES: This AD is effective October 3, 

2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of October 3, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of May 24, 2004 (69 FR 

25481, May 7, 2004). 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P. O. Box 3707, 

MC 2H–65, Seattle, Washington 98124– 

2207; telephone 206–544–5000, 

extension 1; fax 206–766–5680; 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: 

Nancy Marsh, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; phone: 425– 

917–6440; fax: 425–917–6590; email: 

nancy.marsh@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2004–09–32, 

Amendment 39–13622 (69 FR 25481, 

May 7, 2004). That AD applies to the 

specified products. The NPRM 

published in the Federal Register on 

December 29, 2011 (76 FR 81890). That 

NPRM proposed to continue to require 

initial and repetitive inspections of the 

fuselage skin and bear strap at the 

forward upper corner of the L1 entry 

door cutout for cracking, and repair if 

necessary. That NPRM also provided an 

optional terminating action for the 

repetitive inspections. That NPRM also 

proposed to require additional 

inspections for airplanes having repairs 

or preventative modifications installed 

and inspections for certain other 

airplanes. That NPRM also proposed to 

add airplanes to the applicability. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

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