Federal Register / Vol. 75, No. 250 / Thursday, December 30, 2010 / Proposed Rules 82335 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to McDonnell Douglas 

Corporation Model DC–10–10, DC–10–10F, 

and MD–10–10F airplanes; certificated in any 

category; as identified in Boeing Alert 

Service Bulletin DC10–57A156, Revision 1, 

dated March 10, 2010. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 57: Wings. 

Unsafe Condition 

(e) This AD results from reports of three 

instances of fuel leaks in the lower cap splice 

of the wing rear spar at station Xors=409. The 

Federal Aviation Administration is issuing 

this AD to detect and correct cracking on the 

lower cap of the rear spar of the left and right 

wings between stations Xors=417 and the 

outboard edge of the lower cap splice of the 

wing rear spar at station Xors=400, which 

could result in fuel leaks or cracking of the 

lower wing skin and structure, causing 

possible inability to sustain the limit load 

and adversely affecting the structural 

integrity 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. 

Inspection 

(g) Within 1,750 flight cycles after the 

effective date of this AD, do an eddy current 

test high frequency (ETHF) inspection for 

cracking on the lower cap of the rear spar of 

the left and right wings between stations 

Xors=417 and the outboard edge of the lower 

cap splice of the wing rear spar at station 

Xors=400, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin DC10–57A156, Revision 1, 

dated March 10, 2010. 

(1) If no cracking is found, repeat the 

inspection required by paragraph (g) of this 

AD thereafter at intervals not to exceed 1,750 

flight cycles. 

(2) If any cracking is found in the spar cap 

aft leg at the fastener holes, and that cracking 

can be removed by hole enlargement, before 

further flight, do a permanent repair, in 

accordance with Boeing DC–10–10 Service 

Rework Drawing SR10570048, Revision J, 

dated July 16, 2009. Within 1,750 flight 

cycles after doing the applicable permanent 

repair, and thereafter at intervals not to 

exceed 1,750 flight cycles, do an ETHF 

inspection for cracking in accordance with 

Boeing DC–10–10 Service Rework Drawing 

SR10570048, Revision J, dated July 16, 2009. 

If any cracking is found during any 

inspection required by this paragraph, before 

further flight, repair the cracking, in 

accordance with the procedures specified in 

paragraph (i) of this AD. 

(3) If any cracking is found in the spar cap 

aft leg at the fastener holes, and that cracking 

cannot be removed by hole enlargement but 

it does not extend into the vertical leg, before 

further flight, do a permanent repair, in 

accordance with Boeing DC–10–10 Service 

Rework Drawing SR10570048, Revision J, 

dated July 16, 2009. Within 4,550 flight 

cycles after doing a permanent repair, and 

thereafter at intervals not to exceed 4,550 

flight cycles, do ETHF and ultrasonic 

inspections for cracking, in accordance with 

Boeing DC–10–10 Service Rework Drawing 

SR10570048, Revision J, dated July 16, 2009. 

If any cracking is found during any 

inspection required by this paragraph, before 

further flight, repair the cracking, in 

accordance with the procedures specified in 

paragraph (i) of this AD. 

(4) If any cracking is found in the spar cap 

aft leg at fastener holes and that cracking 

extends into the vertical leg of the spar cap, 

do the actions specified in paragraph (g)(4)(i) 

or (g)(4)(ii) of this AD. 

(i) Do the actions in paragraphs (g)(4)(i)(A) 

and (g)(4)(i)(B) of this AD. 

(A) Before further flight, do a temporary 

repair in accordance with Boeing DC–10–10 

Service Rework Drawing SR10570048, 

Revision J, dated July 16, 2009. Within 1,650 

flight cycles after doing the temporary repair; 

and thereafter at intervals not to exceed 1,650 

flight cycles, do ETHF and ultrasonic 

inspections for cracking of the repaired area, 

in accordance with Boeing DC–10–10 Service 

Rework Drawing SR10570048, Revision J, 

dated July 16, 2009, until the permanent 

repair required by paragraph (g)(4)(i)(B) of 

this AD is done. If any cracking is found 

during any inspection required by this 

paragraph, before further flight, repair the 

cracking, in accordance with the procedures 

specified in paragraph (i) of this AD. 

(B) Within 7,000 flight cycles after the 

temporary repair has been done, do the 

applicable permanent repair, in accordance 

with Boeing DC–10–10 Service Rework 

Drawing SR10570019, Revision K, dated 

April 17, 2009. Within 4,550 flight cycles 

after doing the permanent repair; and 

thereafter at intervals not to exceed 4,550 

flight cycles; do ETHF and ultrasonic 

inspections for cracking of the repaired area, 

in accordance with Boeing DC–10–10 Service 

Rework Drawing SR10570019, Revision K, 

dated April 17, 2009. If any cracking is found 

during any inspection required by this 

paragraph, before further flight, repair the 

cracking, in accordance with the procedures 

specified in paragraph (i) of this AD. 

(ii) Before further flight do the applicable 

permanent repair, in accordance with Boeing 

DC–10–10 Service Rework Drawing 

SR10570019, Revision K, dated April 17, 

2009. Within 4,550 flight cycles after doing 

the permanent repair; and thereafter at 

intervals not to exceed 4,550 flight cycles, do 

ETHF and ultrasonic inspections for cracking 

of the repaired area, in accordance with 

Boeing DC–10–10 Service Rework Drawing 

SR10570019, Revision K, dated April 17, 

2009. If any cracking is found during any 

inspection required by this paragraph, before 

further flight, repair the cracking, in 

accordance with the procedures specified in 

paragraph (i) of this AD. 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(h) Actions accomplished before the 

effective date of this AD according to Boeing 

Alert Service Bulletin DC10–57A156, dated 

September 16, 2009, are considered 

acceptable for compliance with the 

corresponding actions specified in this AD. 

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: 

Nenita Odesa, Aerospace Engineer, Airframe 

Branch, ANM–120L, FAA, Los Angeles ACO, 

3960 Paramount Boulevard, Lakewood, 

California 90712–4137; phone: (562) 627– 

5234; fax: (562) 627–5210; e-mail: nenita.

odessa@faa.gov. 

(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. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Los Angeles 

ACO to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane and 14 

CFR 25.571, Amendment 45, and the 

approval must specifically refer to this AD. 

Issued in Renton, Washington, on 

December 17, 2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–33001 Filed 12–29–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1296; Directorate 

Identifier 2010–CE–063–AD] 

RIN 2120–AA64 

Airworthiness Directives; APEX 

Aircraft Model CAP 10 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (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 results from mandatory continuing 

airworthiness information (MCAI) 


srobinson on DSKHWCL6B1PROD with PROPOSALS
82336 Federal Register / Vol. 75, No. 250 / Thursday, December 30, 2010 / Proposed Rules 

originated by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

A fatal accident occurred to a CAP 10C, in 

which the pilot lost control of the aeroplane. 

The following investigation has revealed 

that the probable cause of the accident was 

the improper locking of a turnbuckle (locking 

clip missing) of the flight control cables, and 

the subsequent inadvertent release of the 

pitchup control cable from the turnbuckle. 

The proposed AD would require 

actions that are intended to address the 

unsafe condition described in the MCAI. 

DATES: We must receive comments on 

this proposed AD by February 14, 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 proposed AD, contact Apex 

Aircraft, Bureau de Navigabilite ́, 1 route 

de Troyes, 21121 DAROIS–France, 

telephone: (33) 380 35 65 10; fax: (33) 

380 35 65 15; e-mail: apex-aircraft.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 proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(telephone (800) 647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Sarjapur Nagarajan, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 

Locust, Room 301, Kansas City, 

Missouri 64106; telephone: (816) 329– 

4145; fax: (816) 329–4090. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2010–1296; Directorate Identifier 

2010–CE–063–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 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued AD No.: 2010– 

0233, dated November 26, 2010 

(referred to after this as ‘‘the MCAI’’), to 

correct an unsafe condition for the 

specified products. The MCAI states: 

A fatal accident occurred to a CAP 10C, in 

which the pilot lost control of the aeroplane. 

The following investigation has revealed 

that the probable cause of the accident was 

the improper locking of a turnbuckle (locking 

clip missing) of the flight control cables, and 

the subsequent inadvertent release of the 

pitchup control cable from the turnbuckle. 

For the above described reasons, this AD 

requires repetitive inspections to verify the 

correct installation of the turnbuckles of the 

flight control cables and, if foreseen by the 

applicable design configuration of the 

turnbuckles and found to be missing, to 

restore the locking clip and the safety wire. 

You may obtain further information 

by examining the MCAI in the AD 

docket. 

FAA’s Determination and Requirements 

of the Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with this State of 

Design Authority, they have notified us 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all 

information and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Differences Between This Proposed AD 

and the MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have proposed 

different actions in this AD from those 

in the MCAI in order to follow FAA 

policies. Any such differences are 

highlighted in a Note within the 

proposed AD. 

Costs of Compliance 

We estimate that this proposed AD 

will affect 28 products of U.S. registry. 

We also estimate that it would take 

about 3 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Required 

parts would cost about $100 per 

product. 

Based on these figures, we estimate 

the cost of the proposed AD on U.S. 

operators to be $9,940, or $355 per 

product. 

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 


srobinson on DSKHWCL6B1PROD with PROPOSALS
Federal Register / Vol. 75, No. 250 / Thursday, December 30, 2010 / Proposed Rules 82337 

proposed AD would not have a 

substantial direct effect on the States, on 

the relationship between the national 

Government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this proposed regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); and 

3. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this proposed AD and placed it in the 

AD docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

2. The FAA amends § 39.13 by adding 

the following new AD: 

APEX Aircraft: Docket No. FAA–2010–1296; 

Directorate Identifier 2010–CE–063–AD. 

Comments Due Date 

(a) We must receive comments by February 

14, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to APEX Aircraft 

Model CAP 10 airplanes, all serial numbers, 

certificated in any category. 

Subject 

(d) Air Transport Association of America 

(ATA) Code 27: Flight Controls. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

A fatal accident occurred to a CAP 10C, in 

which the pilot lost control of the aeroplane. 

The following investigation has revealed 

that the probable cause of the accident was 

the improper locking of a turnbuckle (locking 

clip missing) of the flight control cables, and 

the subsequent inadvertent release of the 

pitchup control cable from the turnbuckle. 

For the above described reasons, this AD 

requires repetitive inspections to verify the 

correct installation of the turnbuckles of the 

flight control cables and, if foreseen by the 

applicable design configuration of the 

turnbuckles and found to be missing, to 

restore the locking clip and the safety wire. 

Actions and Compliance 

(f) Unless already done, do the following 

actions: 

(1) Within the next 2 months after the 

effective date of this AD: 

(i) If the turnbuckles are designed to be 

locked with locking clips and safety wire, 

verify that the locking clips are properly 

installed in the corresponding groove, that 

the safety wire of a minimum diameter of 0.8 

millimeter (mm) is correctly installed, and 

that there is no damage to the whole 

turnbuckle installation. 

(ii) For all other designs of turnbuckles, 

verify the correct installation of the safety 

locking devices. 

(iii) If any discrepancy is found during the 

inspection required by paragraph (f)(1)(i) or 

(f)(1)(ii) of this AD, before further flight, 

restore the correct turnbuckle installation in 

accordance with standard maintenance 

practice. 

(2) Repeat the inspection required by 

paragraph (f)(1)(i) or (f)(1)(ii) of this AD, as 

applicable to the turnbuckles design, and the 

associated corrective actions required by 

paragraph (f)(1)(iii) of this AD at intervals not 

to exceed 110 hours time-in-service or 13 

months since the last inspection, whichever 

occurs first. 

FAA AD Differences 

Note: 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: Sarjapur Nagarajan, Aerospace 

Engineer, FAA, Small Airplane Directorate, 

901 Locust, Room 301, Kansas City, Missouri 

64106; telephone: (816) 329–4145; 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 FAAapproved 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 European Aviation 

Safety Agency (EASA) AD No.: 2010–0233, 

dated November 26, 2010, for related 

information. For service information related 

to this AD, contact Apex Aircraft, Bureau de 

Navigabilite ́, 1 route de Troyes, 21121 

DAROIS–France, telephone: (33) 380 35 65 

10; fax: (33) 380 35 65 15; email: apexaircraft.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. 

Issued in Kansas City, Missouri, on 

December 22, 2010. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2010–32966 Filed 12–29–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1271; Directorate 

Identifier 2010–NM–187–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 777–200, –300, and 

–300ER Series 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 installing an auto 

shutoff feature for the center override/ 

jettison fuel pumps, and installing 

power control circuitry for the center 


srobinson on DSKHWCL6B1PROD with PROPOSALS