8620 Federal Register / Vol. 76, No. 31 / Tuesday, February 15, 2011 / Rules and Regulations 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(j) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, 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: 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. 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 

(k) For related information, refer to MCAI 

European Aviation Safety Agency 

Airworthiness Directive 2009–0221R1, dated 

June 30, 2010; and Fokker Service Bulletin 

SBF100–32–158, dated October 2, 2009. 

Material Incorporated by Reference 

(l) You must use Fokker Service Bulletin 

SBF100–32–158, dated October 2, 2009, 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 Fokker Services B.V., 

Technical Services Dept., P.O. Box 231, 2150 

AE Nieuw-Vennep, the Netherlands; 

telephone +31 (0)252–627–350; fax +31 

(0)252–627–211; e-mail 

technicalservices.fokkerservices@stork.com; 

Internet http://www.myfokkerfleet.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 January 

31, 2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–2823 Filed 2–14–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0594; Directorate 

Identifier 98–ANE–43–AD; Amendment 39– 

16604; AD 2011–04–04] 

RIN 2120–AA64 

Airworthiness Directives; Pratt & 

Whitney JT8D–209, –217, –217A, 

–217C, and –219 Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

Pratt & Whitney (PW) JT8D–209, –217, 

–217A, –217C, and –219 turbofan 

engines. That AD currently requires 

revisions to the engine manufacturer’s 

time limits section (TLS) to include 

enhanced inspection of selected critical 

life-limited parts at each piece-part 

opportunity. This new AD modifies the 

TLS of the manufacturer’s engine 

manual and an air carrier’s approved 

continuous airworthiness maintenance 

program to incorporate additional 

inspection requirements. This AD was 

prompted by PW developing, and the 

FAA approving, improved inspection 

procedures for the critical life-limited 

parts. The mandatory inspections are 

needed to identify those critical rotating 

parts with conditions, which if allowed 

to continue in service, could result in 

uncontained failures. We are issuing 

this AD to prevent critical life-limited 

rotating engine part failure, which could 

result in an uncontained engine failure 

and damage to the airplane. 

DATES: This AD is effective March 22, 

2011. 

ADDRESSES: 

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: Ian 

Dargin, Aerospace Engineer, Engine 

Certification Office, FAA, Engine and 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7178, fax: 781–238– 

7199; e-mail: ian.dargin@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2005–18–02, 

Amendment 39–14242 (70 FR 71610, 

November 29, 2005). That AD applies to 

the specified products. The NPRM 

published in the Federal Register on 

August 18, 2010 (75 FR 50945). That 

NPRM proposed to modify the TLS of 

the manufacturer’s engine manual and 

an air carrier’s approved continuous 

airworthiness maintenance program to 

incorporate additional inspection 

requirements. PW has developed and 

the FAA has approved improved 

inspection procedures for the critical 

life-limited parts. The mandatory 

inspections are needed to identify those 

critical rotating parts with conditions 

which, if allowed to continue in service, 

could result in uncontained failures. 

Comment 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comment 

received on the proposal and the FAA’s 

response to the comment. 

Request 

One commenter, American Airlines, 

requested that we change the 


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Federal Register / Vol. 76, No. 31 / Tuesday, February 15, 2011 / Rules and Regulations 8621 

compliance time from within 30 days 

after the effective date of the AD, to 

within 180 days after the effective date 

of the AD. This change would give PW 

the time to revise fan hub inspection 

Alert Service Bulletin No. A6272, dated 

September 24, 1996, to obtain an 

Alternative Method of Compliance to 

fan hub inspection AD 97–17–04R1, and 

to allow automatic eddy current 

inspection per engine manual Section 

72–33–31, Inspection No.–05. 

We agree. Availability of the tooling 

will take about 6 months, and the risk 

will be negligible since a manual 

inspection is now in place. We revised 

this AD as requested. 

Conclusion 

We reviewed the relevant data, 

considered the comment received, and 

determined that air safety and the 

public interest require adopting the AD 

with the change described previously. 

We also determined that this change 

will not increase the economic burden 

on any operator nor increase the scope 

of the AD. 

Costs of Compliance 

We estimate that this AD will affect 

1,143 JT8D–209, –217, –217A, –217C, 

and –219 turbofan engines installed on 

airplanes of U.S. registry. We also 

estimate that it will take about 10 workhours per engine to perform the actions, 

and that the average labor rate is $85 per 

work-hour. Since this is an added 

inspection requirement, included as 

part of the normal maintenance cycle, 

no additional part costs are involved. 

Based on these figures, we estimate the 

total cost of the AD to U.S. operators to 

be $971,550. 

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 

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, 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 Amendment 39–14242 (70 FR 

71610, November 29, 2005), and adding 

the following new AD: 

2011–04–04 Pratt & Whitney: Amendment 

39–16604. Docket No. FAA–2010–0594; 

Directorate Identifier 98–ANE–43–AD. 

Effective Date 

(a) This airworthiness directive (AD) is 

effective March 22, 2011. 

Affected ADs 

(b) This AD supersedes AD 2005–18–02, 

Amendment 39–14242. 

Applicability 

(c) This AD applies to Pratt & Whitney 

(PW) JT8D–209, –217, –217A, –217C, and 

–219 turbofan engines. These engines are 

installed on, but not limited to Boeing 727 

and McDonnell Douglas MD–80 series 

airplanes. 

Unsafe Condition 

(d) This AD results from the need to 

require enhanced inspection of selected 

critical life-limited parts of JT8D–209, –217, 

–217A, –217C, and –219 turbofan engines. 

We are issuing this AD to prevent critical 

life-limited rotating engine part failure, 

which could result in an uncontained engine 

failure and damage to the airplane. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified unless the 

actions have already been done. 

(f) Within the next 180 days after the 

effective date of this AD, (1) revise the Time 

Limits section (TLS) of the manufacturer’s 

engine manual, part number 773128, as 

appropriate for PW JT8D–209, –217, –217A, 

–217C, and –219 turbofan engines, and (2) for 

air carriers, revise the approved mandatory 

inspections section of the continuous 

airworthiness maintenance program, by 

adding the following: 

‘‘Critical Life Limited Part Inspection 

A. Inspection Requirements: 

(1) This section contains the definitions for 

individual engine piece-parts and the 

inspection procedures, which are necessary, 

when these parts are removed from the 

engine. 

(2) It is necessary to do the inspection 

procedures of the piece-parts in Paragraph B 

when: 

(a) The part is removed from the engine 

and disassembled to the level specified in 

paragraph B and 

(b) The part has accumulated more than 

100 cycles since the last piece-part 

inspection, provided that the part is not 

damaged or related to the cause of its 

removal from the engine. 

(3) The inspections specified in this 

section do not replace or make unnecessary 

other recommended inspections for these 

parts or other parts. 

B. Parts Requiring Inspection. 

Note: Piece-part is defined as any of the 

listed parts with all the blades removed. 

Description Section Inspection No. 

Hub (Disk), 1st Stage Compressor: 

* Hub Detail—All P/Ns ..................................................................................................................... 72–33–31 –03, –04, –05 

* Hub Assembly—All P/Ns .............................................................................................................. 72–33–31 –03, –04, –05 

Disk, 13th Stage Compressor—All P/Ns ................................................................................................. 72–36–47 –02 

HP Turbine, First Stage: 

Rotor Assembly—All P/Ns ................................................................................................................ 72–52–02 –04 


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8622 Federal Register / Vol. 76, No. 31 / Tuesday, February 15, 2011 / Rules and Regulations 

Description Section Inspection No. 

Disk—All P/Ns .................................................................................................................................. 72–52–02 –03 

Disk, 2nd Stage Turbine—All P/Ns ......................................................................................................... 72–53–16 –02 

* Disk, 3rd Stage Turbine—All P/Ns ....................................................................................................... 72–53–17 –02, –03 

* Disk, 4th Stage Turbine—All P/Ns ....................................................................................................... 72–53–18 –02, –03 

(g) The parts that have an Engine Manual 

Inspection Task and or Sub Task Number 

reference updated in the table of this AD, are 

identified by an asterisk (*) that precedes the 

part nomenclature. 

(h) Except as provided in paragraph (i) of 

this AD, and notwithstanding contrary 

provisions in section 43.16 of the Federal 

Aviation Regulations (14 CFR 43.16), these 

mandatory inspections shall be performed 

only in accordance with the TLS of the 

manufacturer’s engine manual. 

Alternative Methods of Compliance (AMOC) 

(i) You must perform these mandatory 

inspections using the TLS of the 

manufacturer’s engine manual unless you 

receive approval to use an AMOC under 

paragraph (j) of this AD. Section 43.16 of the 

Federal Aviation Regulations (14 CFR 43.16) 

may not be used to approve alternative 

methods of compliance or adjustments to the 

times in which these inspections must be 

performed. 

(j) The Manager, Engine Certification 

Office, has the authority to approve 

alternative methods of compliance for this 

AD if requested using the procedures found 

in 14 CFR 39.19. 

Maintaining Records of the Mandatory 

Inspections 

(k) You have met the requirements of this 

AD when you revise the TLS of the 

manufacturer’s engine manual as specified in 

paragraph (f) of this AD. For air carriers 

operating under part 121 of the Federal 

Aviation Regulations (14 CFR part 121), you 

have met the requirements of this AD when 

you modify your continuous airworthiness 

maintenance plan to reflect those changes. 

You do not need to record each piece-part 

inspection as compliance to this AD, but you 

must maintain records of those inspections 

according to the regulations governing your 

operation. For air carriers operating under 

part 121, you may use either the system 

established to comply with section 121.369 

or an alternative accepted by your principal 

maintenance inspector if that alternative: 

(1) Includes a method for preserving and 

retrieving the records of the inspections 

resulting from this AD; and 

(2) Meets the requirements of section 

121.369(c); and 

(3) Maintains the records either 

indefinitely or until the work is repeated. 

(l) These record keeping requirements 

apply only to the records used to document 

the mandatory inspections required as a 

result of revising the TLS of the 

manufacturer’s engine manual as specified in 

paragraph (f) of this AD. These record 

keeping requirements do not alter or amend 

the record keeping requirements for any 

other AD or regulatory requirement. 

Related Information 

(m) For more information about this AD, 

contact Ian Dargin, Aerospace Engineer, 

Engine Certification Office, FAA, Engine and 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

e-mail: ian.dargin@faa.gov; phone: 781–238– 

7178, fax: 781–238–7199. 

Issued in Burlington, Massachusetts, on 

February 3, 2011. 

Peter A. White, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–3347 Filed 2–14–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1112; Directorate 

Identifier 2010–NM–051–AD; Amendment 

39–16607; AD 2011–04–07] 

RIN 2120–AA64 

Airworthiness Directives; Fokker 

Services B.V. Model F.28 Mark 0070 

and 0100 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

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: 

The flight crew of a F28 Mark 0070 (Fokker 

70) aeroplane received a MLG [main landing 

gear] unsafe message after landing gear down 

selection during approach. * * * 

Inspection just after landing revealed a lot 

of ice near the LH [left-hand] MLG downlock 

actuator. * * * 

Based on the quantity and location of the 

ice, it is considered highly likely that the ice 

had formed between the upper end of the 

downlock actuator and the upper side brace, 

and was accumulated during taxi on slushand snow-contaminated taxiways and 

runway at the departure airport. 

Ice in this location prevents the actuator 

from turning freely relative to the upper side 

brace during landing gear down selection, 

likely resulting in failure of the piston rod. 

This condition, if not corrected, could lead 

to further cases of MLG extension problems, 

possibly resulting in loss of control of the 

aeroplane during landing roll-out. 

* * * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

March 22, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of March 22, 2011. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: 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. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on November 15, 2010 (75 FR 

69606). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

The flight crew of a F28 Mark 0070 (Fokker 

70) aeroplane received a MLG [main landing 

gear] unsafe message after landing gear down 

selection during approach. After cycling the 

landing gear, only a LH [left-hand] MLG 

unsafe indication remained. A go-around was 

initiated and alternate landing gear down 

selection was performed twice, but the LH 

MLG did not lock down. During final 

approach, without further flight crew action, 

all 3 green lights illuminated and an 

uneventful landing was made. 

Inspection just after landing revealed a lot 

of ice near the LH MLG downlock actuator. 

Further investigation revealed that the piston 

rod of the downlock actuator had failed at the 

threaded end close to the eye end, which is 

attached to the lower lock link, and that the 

piston rod was broken in an overload by 


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