Federal Register / Vol. 76, No. 63 / Friday, April 1, 2011 / Rules and Regulations 18033 

# 2 fire, the fire extinguishing capability 

would not be operational. 

* * * * * 

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. 

Actions 

(g) Within 8 days after the effective date of 

this AD: Visually inspect the extinguishing 

system line and the low pressure bleed line 

of the number 2 engine at frame 42 in the rear 

compartment to determine proper 

installation of the lines, in accordance with 

paragraph 2.B.(1) of the Accomplishment 

Instructions of Dassault Service Bulletin 

F50–519, dated February 18, 2011. 

(1) If the lines are properly installed, no 

further action is required by this paragraph. 

(2) If the lines are improperly installed, 

before further flight, do the actions specified 

in paragraphs (g)(2)(i) and (g)(2)(ii) of this 

AD, in accordance with paragraph 2.B.(1) of 

the Accomplishment Instructions of Dassault 

Service Bulletin F50–519, dated February 18, 

2011. 

(i) Inspect the improperly installed lines 

for deformation. 

(A) If no deformation is found on the 

improperly installed lines, before further 

flight, re-install the lines using the proper 

connections, in accordance with paragraph 

2.B.(1) of the Accomplishment Instructions of 

Dassault Service Bulletin F50–519, dated 

February 18, 2011. 

(B) If any deformation is found on the 

improperly installed lines, before further 

flight, replace the lines in accordance with 

paragraph 2.B.(1) of the Accomplishment 

Instructions of Dassault Service Bulletin 

F50–519, dated February 18, 2011. 

(ii) Verify the correct connection of the 

lines in accordance with paragraph 2.B.(1) of 

the Accomplishment Instructions of Dassault 

Service Bulletin F50–519, dated February 18, 

2011. 

Reporting Requirement 

(h) Submit a report of the findings (both 

positive and negative) of the inspection 

required by paragraph (g) of this AD to 

Dassault Aviation, as specified in paragraph 

2.B.(2) of the Accomplishment Instructions of 

Dassault Service Bulletin F50–519, dated 

February 18, 2011. Submit the report at the 

applicable time specified in paragraph (h)(1) 

or (h)(2) of this AD. The report must include 

the information identified in Dassault Service 

Bulletin F50–519, dated February 18, 2011. 

Under the provisions of the Paperwork 

Reduction Act (44 U.S.C. 3501 et seq.), the 

Office of Management and Budget (OMB) has 

approved the information collection 

requirements contained in this AD and has 

assigned OMB Control Number 2120–0056. 

(1) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 10 days after the inspection. 

(2) If the inspection was done before the 

effective date of this AD: Submit the report 

within 10 days after the effective date of this 

AD. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: No 

Differences. 

Other FAA AD Provisions 

(i) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Tom Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue, SW., Renton, Washington 98057– 

3356; telephone 425–227–1137; fax 425–227– 

1149. Information may be e-mailed to: 

9-ANM-116-AMOC-REQUESTS@faa.gov. 

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/ 

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(3) Reporting Requirements: A federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

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 

(j) Refer to MCAI European Aviation Safety 

Agency Emergency Airworthiness Directive 

2011–0025–E, dated February 18, 2011; and 

Dassault Service Bulletin F50–519, dated 

February 18, 2011; for related information. 

Material Incorporated by Reference 

(k) You must use Dassault Service Bulletin 

F50–519, dated February 18, 2011, to do the 

actions required by this AD, unless the AD 

specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Dassault Falcon Jet, P.O. Box 

2000, South Hackensack, New Jersey 07606; 

telephone 201–440–6700; Internet http:// 

www.dassaultfalcon.com. 

(3) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

(4) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at NARA, call 202–741–6030, or go 

to: http://www.archives.gov/federal_register/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on March 

21, 2011. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–7427 Filed 3–31–11; 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; Amendment 

39–16635; AD 2011–06–10] 

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: Final rule. 

SUMMARY: We are superseding 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. That AD currently 

requires cleaning, inspecting, and 

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 airplanes; 

and inserting a copy of the AD into the 

pilot’s operating handbook (POH) for 

certain airplanes. This new AD retains 


jlentini on DSKJ8SOYB1PROD with RULES
18034 Federal Register / Vol. 76, No. 63 / Friday, April 1, 2011 / Rules and Regulations 

the actions required by the previous AD 

(AD 99–15–04 R1), adds certain Model 

PA–46R–350T airplanes to the 

Applicability section, expands the 

applicability to include other T.I.T. 

systems, and incorporates new service 

information. This AD was prompted by 

the manufacturer revising related 

service information and adding an 

airplane model to the list of affected 

airplanes. We are issuing 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: This AD is effective May 6, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of May 6, 2011. 

ADDRESSES: 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 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: 

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: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 99–15–04 R1, 

Amendment 39–11747 (65 FR 33745, 

May 25, 2000). That AD applies to 

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 

T.I.T. gauge and associated probe. The 

NPRM published in the Federal 

Register on December 30, 2010 (75 FR 

82329). That NPRM proposed to 

continue to require cleaning, inspecting, 

and calibrating the T.I.T. system on 

certain airplanes; replacing any T.I.T. 

system that fails the inspection and 

calibration test; repetitively replacing 

the T.I.T. probe on certain airplanes; 

and inserting a copy of the AD into the 

pilot’s operating handbook (POH). That 

NPRM also proposed to 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. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

Costs of Compliance 

We estimate that this AD affects 898 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Clean and inspect the T.I.T 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 T.I.T. 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 work-hour × $85 per hour = $85 ...... Not applicable ................. 85 85 × 898 affected airplanes = $76,330. 

The requirements of this 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 will be 

required based on the results of the 

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 


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Federal Register / Vol. 76, No. 63 / Friday, April 1, 2011 / Rules and Regulations 18035 

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 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) 

99–15–04 R1, Amendment 39–11747 (65 

FR 33745, May 25, 2000), and adding 

the following new AD: 

2011–06–10 Piper Aircraft, Inc. (Type 

Certificate Previously Held by The New 

Piper Aircraft, Inc.): Amendment 39– 

16635; Docket No. FAA–2010–1295; 

Directorate Identifier 2010–CE–060–AD. 

Effective Date 

(a) This airworthiness directive (AD) is 

effective May 6, 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– 

46–310P, PA–46–350P, and PA–46R–350T 

airplanes that are: 

(1) Certificated in any category; and 

(2) equipped with a turbine inlet 

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

3 of this AD. Relief from this AD is available 

only if the gauge and probe are replaced 

through STC and not if a second T.I.T. gauge 

was installed while retaining the Lewis or 

Transicoil T.I.T. gauge and probe. 

TABLE 1—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. 

TABLE 2—GROUP 2 (AIRPLANES NOT PREVIOUSLY AFFECTED BY AD 99–15–04 R1) 

Models S/N 

PA–46–350P (Malibu Mirage) ............................................................................................................................... 4636021 and subsequent. 

PA–46R–350T (Matrix) .......................................................................................................................................... 4692001 and subsequent. 

TABLE 3—AFFECTED AIRPLANE MODELS AND CORRESPONDING AFFECTED TURBINE INLET TEMPERATURE (T.I.T.) SYSTEM

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. 


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18036 Federal Register / Vol. 76, No. 63 / Friday, April 1, 2011 / Rules and Regulations 

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 T.I.T. 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 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. 

Compliance 

(f) For Group 1 airplanes: Comply with this 

AD within the compliance times specified, 

unless already done. 

TABLE 4—GROUP 1 AIRPLANES (AIRPLANES PREVIOUSLY AFFECTED BY AD 99–15–04 R1) 

Actions Compliance Procedures 

(1) Clean and inspect the T.I.T. gauge and 

probe.

Within the next 100 hours time-in-service 

(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, section 77–20–00 

A.(1)(d), dated July 1, 1998; and Piper Airplane Maintenance Manual PA–46–350P/ 

PA–46R–350T, Part Number 761 876, 

Chapter 77, section 77–20–00 1.C, page 1, 

dated August 28, 2007, and page 2, dated 

July 31, 2008, as applicable. 

(2) Calibrate the T.I.T. 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, section 77–20–00 

A.(1)(g), dated July 1, 1998; and Piper Airplane Maintenance Manual PA–46–350P/ 

PA–46R–350T, Part Number 761 876, 

Chapter 77, section 77–20–00 1.F, page 2, 

dated July 31, 2008, and pages 3 and 4, 

dated August 28, 2007, as applicable; or 

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

(3) If the T.I.T. probe fails the inspection required in paragraph (f)(1) of this AD and/or 

the T.I.T. 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 3 of this AD as long 

as it has been inspected, passed the inspection, and been 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, section 77–20–00 

A.(1)(f), dated July 1, 1998; and Piper Airplane Maintenance Manual PA–46–350P/ 

PA–46R–350T, Part Number 761 876, 

Chapter 77, section 77–20–00 1.E., page 2, 

dated July 31, 2008, as applicable; or Piper 

Service Bulletin No. 995C, dated November 

17, 2009 

(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 3 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 T.I.T. 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 T.I.T. 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, section 

77–20–00 A.(1)(f), dated July 1, 1998; or 

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

For serial numbers 4636001 through 

4636020: Follow Piper Airplane Maintenance Manual PA–46–350P/PA–46R–350T, 

Part Number 761 876, Chapter 77, section 

77–20–00 1.E., page 2, dated July 31, 

2008; 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. 


jlentini on DSKJ8SOYB1PROD with RULES
Federal Register / Vol. 76, No. 63 / Friday, April 1, 2011 / Rules and Regulations 18037 

TABLE 5—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 T.I.T. gauge and probe.

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

PA–46–350P/PA–46R–350T, Part Number 

761 876, Chapter 77, section 77–20–00 

1.C, page 1, dated August 28, 2007, and 

page 2, dated July 31, 2008. 

(2) Model PA–46–350P airplanes, S/Ns 

4636021 through 4636374 only: If the T.I.T. 

probe fails the inspection required in paragraph (g)(1) of this AD, replace any failed 

parts with a serviceable part listed in table 3 

of this AD as long as it has been inspected 

and has passed the inspection.

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

AD.

Follow Piper Service Bulletin No. 995C, dated 

November 17, 2009. 

(3) All Group 2 airplanes: Replace the T.I.T. 

probe with a new part number 686–216 

probe.

Upon accumulating 250 hours TIS on the currently installed T.I.T. 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 3 of this AD after it has been inspected and properly calibrated.As of the effective date of this AD ................... Not applicable. 

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. 

Material Incorporated by Reference 

(j) You must use the service information 

contained in Table 6 of this AD to do the 

actions required by this AD, unless the AD 

specifies otherwise. 

TABLE 6—ALL MATERIAL INCORPORATED BY REFERENCE

Document Revision Date 

Piper Service Bulletin No. 995C ................................................................................................. N/A .................... November 17, 2009. 

Piper Airplane Maintenance Manual PA–46–310P/PA–46–350P, Part Number 761 783, 

Chapter 77, ‘‘Engine Indicating,’’ Section 77–20–00, pages 1 through 4.

N/A ................... July 1, 1998. 

Piper Airplane Maintenance Manual PA–46–350P/PA–46R–350T, Part Number 761 876, 

Chapter 77, ‘‘Engine Indicating,’’ Section 77–20–00, pages 1 through 4.

N/A ................... July 31, 2008. 

Section 77–20–00: pages 1, 3, 

and 4, dated August 28, 

2007; page 2, dated July 

31, 2008. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact 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. 

(3) You may review copies of the 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. 

(4) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at an NARA facility, call 202–741– 

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

federal_register/code_of_federal_regulations/ 

ibr_locations.html. 

Appendix 1 to AD 2011–06–10—Model PA– 

46–310P (Malibu); 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. 


jlentini on DSKJ8SOYB1PROD with RULES
18038 Federal Register / Vol. 76, No. 63 / Friday, April 1, 2011 / Rules and Regulations 

Appendix 2 to AD 2011–06–10—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 March 

9, 2011. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2011–7569 Filed 3–31–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0256; Directorate 

Identifier 2010–NM–114–AD; Amendment 

39–16645; AD 2011–07–08] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A340–200 and –300 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD results 

from mandatory continuing 

airworthiness information (MCAI) 

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: 

Two A340–300 aeroplanes experienced 

one single door opening of engine number 

(n°) 3 Thrust Reverser (TR) pivoting door 

during climb. These events were the result of 

a primary lock malfunction and incorrect 

engagement of the secondary lock. 

* * * * * 

Deployment of one TR door in flight, 

particularly during the take-off or go around, 

could result in heavy buffet at low speed, or 

could significantly reduce take off 

performance [and increase pilot workload 

during takeoff or go around], which would 

constitute an unsafe condition. 

* * * * * 

This AD requires actions that are 

intended to address the unsafe 

condition described in the MCAI. 

DATES: This AD becomes effective April 

18, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of April 18, 2011. 

We must receive comments on this 

AD by May 16, 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, between 

9 a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations 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: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; phone: 425– 

227–1138; fax: 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2010–0044, 

dated March 17, 2010 [corrected March 

25, 2010] (referred to after this as ‘‘the 

MCAI’’), to correct an unsafe condition 

for the specified products. The MCAI 

states: 

Two A340–300 aeroplanes experienced 

one single door opening of engine number 

(n°) 3 Thrust Reverser (TR) pivoting door 

during climb. These events were the result of 

a primary lock malfunction and incorrect 

engagement of the secondary lock. 

While investigations on root cause of these 

events were conducted, preventive actions 

have been required by EASA AD 2008–0074, 

AD 2009–0063 [which corresponds to FAA 

AD 2009–21–05, Amendment 39–16042] and 

AD 2009–0133. 

The root cause has now been identified as 

being a combined failure of the thrust 

reverser pivoting door primary lock and 

actuator. 

Deployment of one TR door in flight, 

particularly during the take-off or go around, 

could result in heavy buffet at low speed, or 

could significantly reduce take off 

performance [and increase pilot workload 

during takeoff or go around], which would 

constitute an unsafe condition. 

Investigations have also identified that 10 

TR pivoting doors of the 16 installed on each 

aeroplane may cause such effects. These are: 

—Outboard engines (n° 1 and 4): all 4 

pivoting doors of each engine. 

—Inboard engines (n° 2 and 3): upper 

inboard pivoting door of each engine. 

In order to reinforce the thrust reverser 

locking mechanism, this AD requires 

installation of a new modified primary lock 

and a new modified actuator on the 10 

critical thrust reverser pivoting doors. 

You may obtain further information 

by examining the MCAI in the AD 

docket. 

Relevant Service Information 

Airbus has issued Mandatory Service 

Bulletin A340–78–4037, including 

Appendices 01 and 02, dated January 

15, 2010; and Mandatory Service 

Bulletin A340–78–4038, Appendices 01 

and 02, dated January 29, 2010. The 

actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. 

FAA’s Determination and Requirements 

of This 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 the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are issuing this 

AD because we evaluated all pertinent 

information and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

There are no products of this type 

currently registered in the United States. 

However, this rule is necessary to 

ensure that the described unsafe 

condition is addressed if any of these 

products are placed on the U.S. Register 

in the future. 


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