## 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

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. 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


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

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 alsoestimate 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


## 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