5066 Federal Register / Vol. 76, No. 19 / Friday, January 28, 2011 / Rules and Regulations 

module in part of a cargo compartment 

or is located directly adjacent to a cargo 

compartment without an intervening 

cargo compartment wall, the following 

applies: 

(a) Any wall of the module (container) 

forming part of the boundary of the 

reduced cargo compartment, subject to 

direct flame impingement from a fire in 

the cargo compartment and including 

any interface item between the module 

(container) and the airplane structure or 

systems, must meet the applicable 

requirements of § 25.855 at Amendment 

25–60. 

(b) Means must be provided so that 

the fire protection level of the cargo 

compartment meets the applicable 

requirements of § 25.855 at Amendment 

25–60, § 25.857 at Amendment 25–60, 

and § 25.858 at Amendment 25–54 

when the module (container) is not 

installed. 

(c) Use of each emergency evacuation 

route must not require occupants of the 

crew rest compartment to enter the 

cargo compartment in order to return to 

the passenger compartment. 

(d) The aural warning in Special 

Condition No. 7 must sound in the crew 

rest compartment in the event of a fire 

in the cargo compartment. 

20. All enclosed stowage 

compartments within the crew rest that 

are not limited to stowage of emergency 

equipment or airplane-supplied 

equipment (e.g., bedding) must meet the 

design criteria given in the table below. 

As indicated by the table below, 

enclosed stowage compartments greater 

than 200 ft3 in interior volume are not 

addressed by this special condition. The 

in-flight accessibility of very large 

enclosed stowage compartments and the 

subsequent impact on the 

crewmember’s ability to effectively 

reach any part of the compartment with 

the contents of a hand fire extinguisher 

will require additional fire protection 

considerations similar to those required 

for inaccessible compartments such as 

Class C cargo compartments. 

Fire protection features 

Stowage compartment interior volumes 

Less than 25 ft3 25 ft3 to 57 ft3 57 ft3 to 200 ft3

Materials of construction 1 ............................................... Yes .................................... Yes .................................... Yes. 

Detectors 2 ....................................................................... No ...................................... Yes .................................... Yes. 

Liner 3 ............................................................................... No ...................................... No ...................................... Yes. 

Locating device 4 ............................................................. No ...................................... Yes .................................... Yes. 

1 Material: The material used to construct each enclosed stowage compartment must at least be fire resistant and must meet the flammability

standards established for interior components according to the requirements of § 25.853. For compartments less than 25 ft3 in interior volume, 

the design must ensure the ability to contain a fire likely to occur within the compartment under normal use. 2 Detectors: Enclosed stowage compartments equal to or exceeding 25 ft3 in interior volume must be provided with a smoke or fire detection 

system to ensure that a fire can be detected within a 1-minute detection time. Flight tests must be conducted to show compliance with this requirement. Each system (or systems) must provide: 

(a) A visual indication in the flight deck within one minute after the start of a fire; 

(b) An aural warning in the crew rest compartment; and 

(c) A warning in the main passenger cabin. This warning must be readily detectable by a flight attendant, taking into consideration the positioning of flight attendants throughout the main passenger compartment during various phases of flight. 3 Liner: If it can be shown that the material used to construct the stowage compartment meets the flammability requirements of a liner for a 

Class B cargo compartment, then no liner would be required for enclosed stowage compartments equal to or greater than 25 ft3 in interior volume but less than 57 ft3 in interior volume. For all enclosed stowage compartments equal to or greater than 57 ft3 in interior volume but less than 

or equal to 200 ft3, a liner must be provided that meets the requirements of § 25.855 at Amendment 25–60 for a Class B cargo compartment. 4 Locating Device: Crew rest areas that contain enclosed stowage compartments exceeding 25 ft3 interior volume, and that are located away 

from one central location, such as the entry to the crew rest area or a common area within the crew rest area, would require additional fire protection features and/or devices to assist the firefighter in determining the location of a fire. 

Issued in Renton, Washington on January 

21, 2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–1730 Filed 1–27–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0593; Directorate 

Identifier 98–ANE–48–AD; Amendment 

39–16584; AD 2011–03–01] 

RIN 2120–AA64 

Airworthiness Directives; Pratt & 

Whitney JT8D–7, –7A, –7B, –9, –9A, 

–11, –15, –15A, –17, –17A, –17R, and 

–17AR Series 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–1, –1A, –1B, 

–7, –7A, –7B, –9, –9A, –11, –15, –15A, 

–17, –17A, –17R, and –17AR series 

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 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 and 

reduce the model applicability. 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 4, 

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. 

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Federal Register / Vol. 76, No. 19 / Friday, January 28, 2011 / Rules and Regulations 5067 

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: We issued 

a notice of proposed rulemaking 

(NPRM) to amend 14 CFR part 39 to 

supersede AD 2005–25–05, Amendment 

39–14398 (70 FR 73361, December 12, 

2005). That AD applies to the specified 

products. The NPRM published in the 

Federal Register on August 18, 2010 

(75 FR 50942). 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 and 

reduce the model applicability. 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. 

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. 

Costs of Compliance 

We estimate that this AD will affect 

1,527 JT8D –7, –7A, –7B, –9, –9A, –11, 

–15, –15A, –17, –17A, –17R, and –17AR 

series 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 $1,297,950. 

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, 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 39–14398 (70 FR 

73361, December 12, 2005), and by 

adding a new airworthiness directive, 

Amendment 39–16584, to read as 

follows: 

2011–03–01 Pratt & Whitney: Amendment 

39–16584. Docket No. FAA–2010–0593; 

Directorate Identifier 98–ANE–48–AD. 

Effective Date 

(a) This airworthiness directive (AD) is 

effective March 4, 2011. 

Affected ADs 

(b) This AD supersedes AD 2005–25–05, 

Amendment 39–14398. 

Applicability 

(c) This AD applies to Pratt & Whitney 

(PW) JT8D–7, –7A, –7B, –9, –9A, –11, –15, 

–15A, –17, –17A, –17R, and –17AR series 

turbofan engines. These engines are installed 

on, but not limited to, Boeing 727 and 737 

series, and McDonnell Douglas DC–9 series 

airplanes. 

Unsafe Condition 

(d) This AD results from the need to 

require enhanced inspection of selected 

critical life-limited parts of PW JT8D series 

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 30 days after the 

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

Limits Section (TLS) of the manufacturer’s 

engine manual, part number 481672, as 

appropriate for PW JT8D–7, –7A, –7B, –9, 

–9A, –11, –15, –15A, –17, –17A, –17R, and 

–17AR series 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 has 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 was not 

damaged or related to the cause for its 

removal from the engine. 

(3) The inspections specified in this 

paragraph do not replace or make not 

necessary 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. 

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5068 Federal Register / Vol. 76, No. 19 / Friday, January 28, 2011 / Rules and Regulations 

Description Section Inspection No. 

Hub (Disk), 1st Stage Compressor: 

* Hub Detail—All P/Ns ...................................................................................................................... 72–33–31 –03, –04, –05, –06 

* Hub Assembly—All P/Ns ............................................................................................................... 72–33–31 –03, –04, –05, –06 

2nd Stage Compressor: 

Disk—All P/Ns .................................................................................................................................. 72–33–33 –02, –03 

Disk Assembly—All P/Ns ................................................................................................................. 72–33–33 –02, –03 

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

HP Turbine Disk, First Stage w/integral Shaft—All P/Ns ........................................................................ 72–52–04 –03 

HP Turbine, First Stage, w/separable Shaft: 

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

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 (Separable), 4th Stage Turbine—All P/Ns .................................................................................... 72–53–15 –02, –03 

Disk (Integral Disk/Hub), 4th Stage Turbine—All P/Ns ........................................................................... 72–53–18 –02’’ 

(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; 

phone (781) 238–7178, fax (781) 238–7199; 

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

Issued in Burlington, Massachusetts, on 

January 24, 2011. 

Thomas A. Boudreau, 

Acting Assistant Manager, Engine and 

Propeller Directorate, Aircraft Certification 

Service. 

[FR Doc. 2011–1869 Filed 1–27–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2010–0688; Airspace 

Docket No. 09–AGL–23] 

RIN 2120–AA66 

Establishment of Low Altitude Area 

Navigation Routes (T–281, T–283, 

T–285, T–286, and T–288); Nebraska 

and South Dakota 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This action establishes five 

low altitude Area Navigation (RNAV) 

routes, designated T–281, T–283, T–285, 

T–286, and T–288, over Nebraska and 

South Dakota; controlled by Denver Air 

Route Traffic Control Center (ARTCC) 

and Minneapolis ARTCC. T-routes are 

low altitude Air Traffic Service routes, 

based on RNAV, for use by aircraft that 

have instrument flight rules (IFR) 

approved Global Positioning System 

(GPS)/Global Navigation Satellite 

System (GNSS) equipment. This action 

enhances safety and improves the 

efficient use of the navigable airspace 

within Denver and Minneapolis ARTCC 

airspace. 

DATES: Effective date 0901 UTC, May 5, 

2011. The Director of the Federal 

Register approves this incorporation by 

reference action under 1 CFR part 51, 

subject to the annual revision of FAA 

Order 7400.9 and publication of 

conforming amendments. 

FOR FURTHER INFORMATION CONTACT: 

Colby Abbott, Airspace, Regulations and 

ATC Procedures Group, Office of 

Airspace Services, Federal Aviation 

Administration, 800 Independence 

Avenue, SW., Washington, DC 20591; 

telephone: (202) 267–8783. 

SUPPLEMENTARY INFORMATION: 

History 

On August 5, 2010, the FAA 

published in the Federal Register a 

notice of proposed rulemaking (NPRM) 

to establish five low altitude RNAV 

routes within Denver and Minneapolis 

ARTCC airspace (75 FR 47252). 

Previously, the pilot’s only options are 

to either fly Visual Flight Rules (VFR), 

VFR-On-Top, file a flight plan with an 

altitude high enough for air traffic 

control to maintain radar surveillance 

and communication frequency coverage, 

or fly many miles out of their way to use 

established airways. Interested parties 

were invited to participate in this 

rulemaking effort by submitting written 

comments on the proposal. One 

comment was received, from the 

Aircraft Owners and Pilots Association, 

supporting the proposal. 

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