Federal Register / Vol. 75, No. 250 / Thursday, December 30, 2010 / Proposed Rules 82329 

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 

(i) Refer to MCAI European Aviation Safety 

Agency Airworthiness Directive 2010–0031, 

dated March 3, 2010; and Dassault 

Mandatory Service Bulletin 7X–065, dated 

July 24, 2009; for related information. 

Issued in Renton, Washington, on 

December 17, 2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–32999 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–2010–1295; Directorate 

Identifier 2010–CE–060–AD] 

RIN 2120–AA64 

Airworthiness Directives; Piper 

Aircraft, Inc. (Type Certificate 

Previously Held by The New Piper 

Aircraft, Inc.) Models PA–46–310P, PA– 

46–350P, and PA–46R–350T Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede an 

existing airworthiness directive (AD) 

that applies to certain Piper Aircraft, 

Inc. Models PA–46–310P and PA–46– 

350P airplanes that are equipped with a 

Lewis or Transicoil turbine inlet 

temperature (T.I.T.) gauge and 

associated probe. The existing AD 

currently requires calibrating the T.I.T. 

system; replacing any T.I.T. system that 

fails the calibration test; repetitively 

replacing the T.I.T. probe on certain 

Model PA–46–350P airplanes; and 

inserting a copy of the AD into the 

pilot’s operating handbook (POH) for 

certain airplanes. Since we issued that 

AD, the manufacturer has revised 

related service information and added 

an airplane model to the list of affected 

airplanes. This proposed AD would 

retain the actions required by AD 99– 

15–04 R1, add certain Model PA–46R– 

350T airplanes to the Applicability 

section, expand the applicability to 

include other T.I.T. systems, and 

incorporate new service information. 

We are proposing this AD to prevent 

improper engine operation caused by 

improperly calibrated T.I.T. indicators 

or defective T.I.T. probes, which could 

result in engine damage/failure with 

consequent loss of control of the 

airplane. 

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: 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 AD, contact Piper Aircraft, Inc., 

2926 Piper Drive, Vero Beach, Florida 

32960; telephone: (772) 567–4361; fax: 

(772) 978–6573; Internet: http:// 

www.newpiper.com/company/ 

publications.asp. You may review 

copies of the referenced service 

information at the FAA, Small Airplane 

Directorate, 901 Locust St., 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 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Darby Mirocha, Aerospace Engineer, 

FAA, Atlanta Aircraft Certification 

Office, 1701 Columbia Avenue, College 

Park, Georgia 30337; phone: (404) 474– 

5573; fax: (404) 474–5605; e-mail: 

darby.mirocha@faa.gov. 

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–2010–1295; Directorate Identifier 

2010–CE–060–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 

On May 17, 2000, we issued AD 99– 

15–04 R1, Amendment 39–11747 (65 FR 

33745, May 25, 2000), for certain Piper 

Aircraft, Inc. (type certificate previously 

held by The New Piper Aircraft, Inc.) 

Models PA–46–310P and PA–46–350P 

airplanes that are equipped with a 

Lewis or Transicoil turbine inlet 

temperature (T.I.T.) gauge and 

associated probe. That AD required 

calibrating the T.I.T. system; replacing 

any T.I.T. system that fails the 

calibration test; repetitively replacing 

the T.I.T. probe on Model PA–46–350P 

airplanes; and inserting a copy of the 

AD into the Emergency Procedures 

section of the POH for certain airplanes. 

That AD resulted from field reports that 

indicated service accuracy problems 

with the existing T.I.T. system on 

certain Piper Aircraft, Inc. Models PA– 

46–310P and PA–46–350P. We issued 

that AD to prevent improper engine 

operation caused by improperly 

calibrated T.I.T. indicators or defective 

T.I.T. probes, which could result in 

engine damage/failure with consequent 

loss of control of the airplane. 

Actions Since Existing AD Was Issued 

Since we issued AD 99–15–04 R1, the 

manufacturer has revised related service 

information and has added an airplane 

model to the list of affected airplanes. 

We have also determined that the scope 

of this proposed AD goes beyond only 

airplanes equipped with Lewis or 

Transicoil gauges and/or probes. 

Relevant Service Information 

We reviewed Piper Aircraft, Inc. 

Service Bulletin No. 995C, dated 


srobinson on DSKHWCL6B1PROD with PROPOSALS
82330 Federal Register / Vol. 75, No. 250 / Thursday, December 30, 2010 / Proposed Rules 

November 17, 2009. The service 

information describes procedures for 

calibrating the T.I.T. system and 

replacing the probe. 

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 retain the 

requirements of AD 99–15–04 R1. This 

proposed AD would also add certain 

Model PA–46R–350T airplanes to the 

Applicability section, expand the 

applicability to include other T.I.T. 

systems, and incorporate new service 

information. 

Costs of Compliance 

We estimate that this proposed AD 

affects 898 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product Cost on U.S. operators 

Clean and inspect the turbine inlet temperature gauge and probe for certain 

Models PA–46–310P and PA–46– 

350P airplanes.

1 work-hour × $85 

per hour = $85.

Not applicable ......... $85 $85 × 780 affected airplanes = $66,300. 

Calibrate the turbine inlet temperature 

gauge for certain Models PA–46–310P 

and PA–46–350P airplanes.

4 work-hours × $85 

per hour = $340.

Not applicable ......... 340 $340 × 427 affected airplanes = 

$145,180. 

Incorporate emergency procedures into 

POH.

1 workhour × $85 

per hour = $85.

Not applicable ......... 85 $85 × 898 affected airplanes = $76,330. 

The requirements of this proposed AD 

add no additional economic burden 

other than the addition of an airplane 

model to the Applicability section. 

We estimate the following costs to do 

any necessary replacements that would 

be required based on the results of the 

proposed inspection. We have no way of 

determining the number of aircraft that 

might need these replacements: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Replace probe ........................................................................................... 1 work-hour × $85 per hour = $85. $384 $469 

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 have determined that this 

proposed AD would not have federalism 

implications under Executive Order 

13132. This proposed AD would not 

have a substantial direct effect on the 

States, on the relationship between the 

national Government and the States, or 

on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that the proposed regulation: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

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

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979), 

(3) Will not affect intrastate aviation 

in Alaska, 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 

removing airworthiness directive (AD) 

99–15–04 R1, Amendment 39–11747 (65 

FR 33745, May 25, 2000), and adding 

the following new AD: 

Piper Aircraft, Inc. (Type Certificate 

Previously Held by The New Piper 

Aircraft, Inc.): Docket No. FAA–2010– 

1295; Directorate Identifier 2010–CE– 

060–AD. 

Comments Due Date 

(a) The FAA must receive comments on 

this AD action by February 14, 2011. 

Affected ADs 

(b) This AD supersedes AD 99–15–04 R1, 

Amendment 39–11747. 

Applicability 

(c) This AD applies to the following Piper 

Aircraft, Inc. (type certificate previously held 

by The New Piper Aircraft, Inc.) Models PA– 


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Federal Register / Vol. 75, No. 250 / Thursday, December 30, 2010 / Proposed Rules 82331 

46–310P, PA–46–350P, and PA–46R–350T 

airplanes that: 

(1) Are certificated in any category; and 

(2) Equipped with a turbine inlet 

temperature (T.I.T.) system identified in table 

1 of this AD. Relief from this AD is available 

only if the gauge and probe are replaced 

through STC and not if a second turbine inlet 

temperature gauge was installed while 

retaining the Lewis or Transicoil T.I.T. gauge 

and probe. 

GROUP 1—AIRPLANES PREVIOUSLY

AFFECTED BY AD 99–15–04 R1 

Models Serial Numbers (S/N) 

PA–46–310P 

(Malibu).

46–8408001 through 46– 

8608067 and 4608001 

through 4608140. 

PA–46–350P 

(Malibu Mirage).

4622001 through 4622200 

and 4636001 through 

4636020. 

GROUP 2—AIRPLANES NOT PREVIOUSLY AFFECTED BY AD 99–15– 

04 R1 

Models Serial Numbers (S/N) 

PA–46–350P 

(Malibu Mirage).

4636021 and subsequent. 

PA–46R–350T 

(Matrix).

4692001 and subsequent. 

TABLE 1—AFFECTED AIRPLANE MODELS AND CORRESPONDING AFFECTED LEWIS OR TRANSICOIL PART NUMBERS (P/NS) 

Models S/N Indication System P/N Probe P/N 

PA–46–310P ............... 46–8408001 through 46–8608067 and 

4608001 through 4608140. 

Lewis T.I.T. analog indicators P/N 471–008 .. 471–009 or 481–387. 

PA–46–350P ............... 4622001 through 4622200 and 4636001 

through 4636020.

Lewis T.I.T. analog indicators P/N 471–008 .. 481–389 or 481–392 

or 686–216 (preferred). 

PA–46–350P ............... 4636021 through 4636374 .............................. Lewis T.I.T. digital indicators P/N 548–811 .... 481–389 or 481–392 

or 686–216 (preferred). 

PA–46–350P ............... 4636375 and subsequent ............................... Avidyne Entegra or other Electronic Flight Information System (EFIS) display.686–216. 

PA–46R–350T ............. 4692001 and subsequent ............................... Avidyne Entegra or other EFIS display .......... 686–216. 

Subject 

(d) Joint Aircraft System Component 

(JASC)/Air Transport Association (ATA) of 

America Code 77, Engine Indicating. 

Unsafe Condition 

(e) This AD was prompted by field reports 

that indicated service accuracy problems 

with the existing turbine inlet temperature 

system on certain Models PA–46–310P, PA– 

46–350P, and PA–46R–350T airplanes. We 

are issuing this AD to prevent improper 

engine operation caused by improperly 

calibrated turbine inlet temperature 

indicators or defective turbine inlet 

temperature probes, which could result in 

engine damage/failure with consequent loss 

of control of the airplane. 

Compliance 

(f) For Group 1 airplanes: Comply with this 

AD within the compliance times specified, 

unless already done. 

TABLE 2—GROUP 1 AIRPLANES

[Airplanes previously affected by AD 99–15–04 R1] 

Actions Compliance Procedures 

(1) Clean and inspect the turbine 

inlet temperature gauge and 

probe.

Within the next 100 hours time-inservice (TIS) after August 31, 

1999 (the effective date retained 

from AD 99–15–04).

Follow Piper Airplane Maintenance Manual 

PA–46–310P/PA–46–350P Part Number 761–783, Chapter 77–20– 

00, section A.(1)(d), pages 1 and 2; and Piper Airplane Maintenance Manual PA–46–350P Part Number 761–876, Chapter 77– 

20–00, section 1.C, pages 1 and 2, as applicable. 

(2) Calibrate the turbine inlet temperature system.Within the next 100 hours TIS 

after August 31, 1999 (the effective date retained from AD 99– 

15–04).

Follow Piper Airplane Maintenance Manual 

PA–46–310P/PA–46–350P Part Number 761–783, Chapter 77–20– 

00, section A.(1)(g), pages 3 and 4; and Piper Airplane Maintenance Manual PA–46–350P Part Number 761–876, Chapter 77– 

20–00, section 1.F, pages 2 through 4, as applicable; or Piper 

Service Bulletin No. 995C, dated November 17, 2009. 

(3) If the turbine inlet temperature 

probe fails the inspection required in paragraph (f)(1) of this 

AD and/or the turbine inlet temperature system indicator cannot 

be calibrated as required in paragraph (f)(2) of this AD, replace 

any failed parts with a serviceable part listed in table 1 of this 

AD as long as it has been inspected and properly calibrated.

Before further flight after the 

cleaning and inspection required 

in paragraph (f)(1) and the calibration required in paragraph 

(f)(2) of this AD.

Follow Piper Airplane Maintenance Manual 

PA–46–310P/PA–46–350P Part Number 761–783, Chapter 77–20– 

00, section A.(1)(f), page 2; and Piper Airplane Maintenance Manual PA–46–350P Part Number 761–876, Chapter 77–20–00, section 1.E., page 2, as applicable; or Piper Service Bulletin No. 995C, 

dated November 17, 2009. 


srobinson on DSKHWCL6B1PROD with PROPOSALS
82332 Federal Register / Vol. 75, No. 250 / Thursday, December 30, 2010 / Proposed Rules 

TABLE 2—GROUP 1 AIRPLANES—Continued 

[Airplanes previously affected by AD 99–15–04 R1] 

Actions Compliance Procedures 

(4) Incorporate the information from 

Appendix 1 and Appendix 2, as 

applicable, of this AD into the 

Emergency Procedures section 

of the pilot operating handbook 

(POH). This may be done by inserting a copy of this AD into the 

POH.

Within the next 100 hours TIS 

after August 31, 1999 (the effective date retained from AD 99– 

15–04).

Not applicable. 

(5) Only install a part listed in table 

1 of this AD after it has been inspected and properly calibrated.

As of July 28, 2000 (the effective 

date of AD 99–15–04 R1).

Not applicable. 

(6) Model PA–46–350P airplanes 

only: Replace the turbine inlet 

temperature probe with a new 

part number 481–389, 481–392, 

or 686–216 probe preferred). 

This action is not required for 

Model PA–46–310P.

Upon accumulating 250 hours TIS 

on the currently installed turbine 

inlet temperature probe or within 

the next 100 hours TIS after August 31, 1999 (the effective date 

retained from AD 99–15–04), 

whichever occurs later, and 

thereafter at intervals not to exceed 250 hours TIS.

For serial numbers 4622001 through 4622200: Follow Piper Airplane 

Maintenance Manual PA–46–310P/PA–46–350P Part Number 

761–783, Chapter 77–20–00, section A.(1)(f), page 2; or Piper 

Service Bulletin No. 995C, dated November 17, 2009. 

For serial numbers 4636001 through 4636020: Follow Piper Airplane 

Maintenance Manual PA–46–350P Part Number 761–876, Chapter 

77–20–00, section 1.E., page 2: or Piper Service Bulletin No. 

995C, dated November 17, 2009. 

(g) For Group 2 airplanes: Comply with 

this AD within the compliance times 

specified, unless already done. 

TABLE 3—GROUP 2 AIRPLANES

[Airplanes not previously affected by AD 99–15–04 R1] 

Actions Compliance Procedures 

(1) Model PA–46–350P airplanes, S/Ns 

4636021 through 4636374 only: Clean and 

inspect the turbine inlet temperature gauge 

and probe.

Within the next 100 hours TIS after the effective date of this AD.Follow Piper Airplane Maintenance Manual 

PA–46–350P Part Number 761–876, Chapter 77–20–00, section 1.C, pages 1 and 2, 

as applicable. 

(2) Model PA–46–350P airplanes, S/Ns 

4636021 through 4636374 only: If the turbine 

inlet temperature probe fails the inspection 

required in paragraph (g)(1) of this AD and/or 

the turbine inlet temperature system indicator 

cannot be calibrated as required in paragraph 

(g)(2) of this AD, replace any failed parts with 

a serviceable part listed in table 1 of this AD 

as long as it has been inspected and properly calibrated.

Before further flight after the cleaning and inspection required in paragraph (g)(1) and 

the calibration required in paragraph (g)(2) 

of this AD.

Follow Piper Service Bulletin No. 995C, dated 

November 17, 2009. 

(3) All Group 2 airplanes: Replace the turbine 

inlet temperature probe with a new part number 686–216 probe.

Upon accumulating 250 hours TIS on the currently installed turbine inlet temperature 

probe or within the next 100 hours TIS after 

the effective date of this AD, whichever occurs later, and thereafter at intervals not to 

exceed 250 hours TIS.

Piper Service Bulletin No. 995C, dated November 17, 2009. 

(4) All Group 2 airplanes: Incorporate the information from Appendix 2 of this AD into the 

Emergency Procedures section of the POH. 

This may be done by inserting a copy of this 

AD into the POH.

Within the next 100 hours TIS after the effective date of this AD.Not applicable. 

(5) All Group 2 airplanes: Only install a part 

listed in table 1 of this AD after it has been 

inspected and properly calibrated.

As of the effective date of this AD ................... Not applicable. 


srobinson on DSKHWCL6B1PROD with PROPOSALS
Federal Register / Vol. 75, No. 250 / Thursday, December 30, 2010 / Proposed Rules 82333 

Alternative Methods of Compliance 

(AMOCs) 

(h)(1) The Manager, Atlanta Aircraft 

Certification Office, 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 99–15–04 R1 

are approved as AMOCs for this AD. 

Related Information 

(i) For more information about this AD, 

contact Darby Mirocha, Aerospace Engineer, 

FAA, Atlanta Aircraft Certification Office, 

1701 Columbia Avenue, College Park, 

Georgia 30337; phone: (404) 474–5573; fax: 

(404) 474–5605; e-mail: 

darby.mirocha@faa.gov. 

(j) For service information identified in this 

AD, contact Piper Aircraft, Inc., 2926 Piper 

Drive, Vero Beach, Florida 32960; telephone: 

(772) 567–4361; fax: (772) 978–6573; 

Internet: http://www.piper.com/home/pages/ 

publications.cfm. You may review copies of 

the referenced service information at the 

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. 

Appendix 1 to Docket No. FAA–2010–1295 

Model PA–46–310P (Mailbu)—Emergency 

Procedures for the Pilot’s Operating 

Handbook (POH) 

(1) If the turbine inlet temperature 

indication fails or is suspected of failure 

during takeoff, climb, descent, or landing, 

maintain FULL RICH mixture to assure 

adequate fuel flow for engine cooling. 

(2) If the turbine inlet temperature 

indication fails or is suspected of failure after 

cruise power has been set, maintain cruise 

power setting and lean to 6 gallons per hour 

(GPH) fuel flow above that specified in the 

Power Setting Table in Section 5 of the AFM/ 

POH. Continually monitor engine cylinder 

head and oil temperatures to avoid exceeding 

temperature limits. 

Appendix 2 to Docket No. FAA–2010–1295 

Model PA–46–350P (Malibu Mirage) and 

Model PA–46R–350T (Matrix)—Emergency 

Procedures for the Pilot’s Operating 

Handbook (POH) 

(1) If the turbine inlet temperature 

indication fails or is suspected of failure 

during takeoff, climb, descent or landing, set 

power per the POH Section 5 Power Setting 

Table and then lean to the approximate POH 

Power Setting Table fuel flow plus 4 GPH. 

(2) If the turbine inlet temperature 

indication fails or is suspected of failure after 

cruise power has been set, maintain the 

power setting and increase indicated fuel 

flow by 1 GPH. Continually monitor engine 

cylinder head and oil temperatures to avoid 

exceeding temperature limits. 

Issued in Kansas City, Missouri on 

December 22, 2010. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2010–32959 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–2010–1206; Directorate 

Identifier 2009–NM–216–AD] 

RIN 2120–AA64 

Airworthiness Directives; McDonnell 

Douglas Corporation Model DC–10–10, 

DC–10–10F, and MD–10–10F Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Model DC–10–10, DC–10–10F, and MD– 

10–10F airplanes. This proposed AD 

would require repetitive inspections 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; temporary 

and permanent repairs if necessary; and 

repetitive inspections of repaired areas 

and corrective actions if necessary. This 

proposed AD results from reports of 

three instances of fuel leaks in the lower 

cap splice of the wing rear spar at 

station Xors=409. We are proposing 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 

of the structure to sustain the limit load 

adversely affecting the structural 

integrity of the airplane. 

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 Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, 3855 

Lakewood Boulevard, MC D800–0019, 

Long Beach, California 90846–0001; 

telephone 206–544–5000, extension 2; 

fax 206–766–5683; e-mail dse.boecom@

boeing.com; Internet https://www.my

boeingfleet.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 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: 

Nenita Odesa, Aerospace Engineer, 

Airframe Branch, ANM–120L, FAA, Los 

Angeles Aircraft Certification Office, 

3960 Paramount Boulevard, Lakewood, 

California 90712–4137; phone: (562) 

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

nenita.odesa@faa.gov. 

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–2010–1206; Directorate Identifier 

2009–NM–216–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. 


srobinson on DSKHWCL6B1PROD with PROPOSALS