Federal Register / Vol. 71, No. 150 / Friday, August 4, 2006 / Rules and Regulations 44185 

parameters for the aircraft and must be 

limitations. 

A minimum takeoff temperature 

limitation will be determined by testing 

to establish the minimum cold-soaked 

temperature at which the airplane can 

operate. The minimum operating 

temperature will be determined by 

testing to establish the minimum 

operating temperature acceptable after 

takeoff from the minimum takeoff 

temperature. If low temperature limits 

are not established by testing, then a 

minimum takeoff and operating fuel 

temperature limit of 5 °F above the 

gelling temperature of Jet A will be 

imposed along with a display in the 

cockpit of the fuel temperature. Fuel 

temperature sensors will be located in 

the coldest part of the tank if applicable. 

13. Powerplant Installation—

Vibration levels: Vibration levels 

throughout the engine operating range 

must be evaluated and: 

(1) Vibration levels imposed on the 

airframe must be less than or equivalent 

to those of the gasoline engine; or 

(2) Any vibration level that is higher 

than that imposed on the airframe by 

the replaced gasoline engine must be 

considered in the modification and the 

effects on the technical areas covered by 

the following paragraphs must be 

investigated: 

14 CFR part 23, §§ 23.251; 23.613; 

23.627; 23.629 (or CAR 3.159, as 

applicable to various models); 23.572; 

23.573; 23.574 and 23.901. 

Vibration levels imposed on the 

airframe can be mitigated to an 

acceptable level by utilization of 

isolators, dampers, clutches and similar 

provisions, so that unacceptable 

vibration levels are not imposed on the 

previously certificated structure. 

14. Powerplant Installation—One 

cylinder inoperative: It must be shown 

by test or analysis, or by a combination 

of methods, that the airframe can 

withstand the shaking or vibratory 

forces imposed by the engine if a 

cylinder becomes inoperative. Diesel 

engines of conventional design typically 

have extremely high levels of vibration 

when a cylinder becomes inoperative. 

No unsafe condition will exist in the 

case of an inoperative cylinder before 

the engine can be shut down. The 

resistance of the airframe structure, 

propeller, and engine mount to shaking 

moment and vibration damage must be 

investigated. It must be shown by test or 

analysis, or by a combination of 

methods, that shaking and vibration 

damage from the engine with an 

inoperative cylinder will not cause a 

catastrophic airframe, propeller, or 

engine mount failure. 

15. Powerplant Installation—High 

Energy Engine Fragments: It may be 

possible for diesel engine cylinders (or 

portions thereof) to fail and physically 

separate from the engine at high velocity 

(due to the high internal pressures). 

This failure mode will be considered 

possible in engine designs with 

removable cylinders or other nonintegral block designs. The following is 

required: 

(1) It must be shown by the design of 

the engine, that engine cylinders, other 

engine components or portions thereof 

(fragments) cannot be shed or blown off 

of the engine in the event of a 

catastrophic engine failure; or 

(2) It must be shown that all possible 

liberated engine parts or components do 

not have adequate energy to penetrate 

engine cowlings; or 

(3) Assuming infinite fragment 

energy, and analyzing the trajectory of 

the probable fragments and components, 

any hazard due to liberated engine parts 

or components will be minimized and 

the possibility of crew injury is 

eliminated. Minimization must be 

considered during initial design and not 

presented as an analysis after design 

completion. 

Issued in Kansas City, Missouri on July 27, 

2006. 

James E. Jackson, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E6–12663 Filed 8–3–06; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 97–ANE–44–AD; Amendment 

39–14705; AD 2006–16–05] 

RIN 2120–AA64 

Airworthiness Directives; Pratt & 

Whitney PW4164, PW4168, and 

PW4168A Series Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD) for 

Pratt & Whitney PW4164, PW4168, and 

PW4168A series turbofan engines. That 

AD currently requires initial and 

repetitive torque checks for loose or 

broken front pylon mount bolts made 

from INCO 718 material and MP159 

material, and initial and repetitive 

visual inspections of the primary mount 

thrust load path. This AD requires the 

same actions, but at reduced intervals 

for front pylon mount bolts made from 

MP159 material. This AD results from 

analysis by the manufacturer that the 

MP159 material pylon bolts do not meet 

the full life cycle torque check interval 

requirement, in a bolt-out condition. We 

are issuing this AD to prevent front 

pylon mount bolt and primary mount 

thrust load path failure, which could 

result in an engine separating from the 

airplane. 

DATES: This AD becomes effective 

September 8, 2006. The Director of the 

Federal Register approved the 

incorporation by reference of certain 

publications listed in the regulations as 

of September 8, 2006. The Director of 

the Federal Register previously 

approved the incorporation by reference 

of certain publications listed in the 

regulations as of February 6, 2003 (68 

FR 28, January 2, 2003). 

ADDRESSES: Contact Pratt & Whitney, 

400 Main St., East Hartford, CT 06108; 

telephone (860) 565–7700, fax (860) 

565–1605 for the service information 

identified in this AD. 

You may examine the AD docket at 

the FAA, New England Region, Office of 

the Regional Counsel, 12 New England 

Executive Park, Burlington, MA. You 

may examine the service information, at 

the FAA, New England Region, Office of 

the Regional Counsel, 12 New England 

Executive Park, Burlington, MA. 

FOR FURTHER INFORMATION CONTACT: 

Barbara Caufield, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

and Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; telephone (781) 238–7146, fax 

(781) 238–7199. 

SUPPLEMENTARY INFORMATION: The FAA 

proposed to amend 14 CFR part 39 with 

a proposed AD. The proposed AD 

applies to Pratt & Whitney PW4164, 

PW4168, and PW4168A series turbofan 

engines. We published the proposed AD 

in the Federal Register on December 29, 

2005 (70 FR 77075). That action 

proposed to require initial and 

repetitive torque checks for loose or 

broken front pylon mount bolts made 

from INCO 718 material and MP159 

material. That action also proposed to 

require initial and repetitive visual 

inspections of the primary mount thrust 

load path, but at reduced intervals from 

AD 2000–16–02R1 for front pylon 

mount bolts made from MP159 material. 

Examining the AD Docket 

You may examine the AD Docket 

(including any comments and service 

information), by appointment, between 

8 a.m. and 4:30 p.m., Monday through 


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44186 Federal Register / Vol. 71, No. 150 / Friday, August 4, 2006 / Rules and Regulations 

Friday, except Federal holidays. See 

ADDRESSES for the location. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We received no 

comments on the proposal or on the 

determination of the cost to the public. 

Bolt Life Limit Clarification 

For clarification, we removed three 

bolt life limit references from 

paragraphs (f)(1), (f)(2), and (f)(3) and 

added paragraph (f)(4). The added 

paragraph states to remove from service 

front pylon mount bolts P/N 54T670, at 

or before reaching the life limit of 

11,000 CSN. 

Conclusion 

We have carefully reviewed the 

available data and determined that air 

safety and the public interest require 

adopting the AD with the changes 

described previously. 

Costs of Compliance 

About 60 engines installed on 

airplanes of U.S. registry are affected by 

this AD. We estimate that it will take 

about four work-hours per engine to 

perform the actions, and that the 

average labor rate is $65 per work-hour. 

Required parts will cost about $26,500 

per engine. Based on these figures, we 

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

operators to be $1,605,600. 

Special Flight Permits Paragraph 

Removed 

Paragraph (g) of the AD we are 

superseding, AD 2000–16–02R1, 

contains a paragraph pertaining to 

special flight permits. Even though this 

final rule does not contain a similar 

paragraph, we have made no changes 

with regard to the use of special flight 

permits to operate the airplane to a 

repair facility to do the work required 

by this AD. In July 2002, we published 

a new Part 39 that contains a general 

authority regarding special flight 

permits and airworthiness directives. 

See Docket No. FAA–2004–8460, 

Amendment 39–9474 (69 FR 47998, July 

22, 2002). Thus, when we now 

supersede ADs we will not include a 

specific paragraph on special flight 

permits unless we want to limit the use 

of that general authority granted in 

section 39.23. 

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); and 

(3) 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. 

We prepared a summary of the costs 

to comply with this AD and placed it in 

the AD Docket. You may get a copy of 

this summary by sending a request to us 

at the address listed under ADDRESSES. 

Include ‘‘AD Docket No. 97–ANE–44–

AD’’ in your request. 

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 Federal Aviation Administration 

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 39–12989 (68 FR 

28, January 2, 2003) and by adding a 

new airworthiness directive, 

Amendment 39–14705, to read as 

follows: 

2006–16–05 Pratt & Whitney: Amendment 

39–14705. Docket No. 97–ANE–44–AD. 

Effective Date 

(a) This AD becomes effective September 8, 

2006. 

Affected ADs 

(b) This AD supersedes AD 2000–16–02R1. 

Applicability 

(c) This AD applies to Pratt & Whitney 

(PW) PW4164, PW4168, and PW4168A series 

turbofan engines, with front pylon mount 

bolts, part number (P/N) 54T670 or 51U615, 

installed. These engines are installed on, but 

not limited to, Airbus A330 series airplanes. 

Unsafe Condition 

(d) This AD results from analysis by the 

manufacturer that MP159 material pylon 

bolts do not meet the full life cycle torque 

check interval requirement, in a bolt-out 

condition. We are issuing this AD to prevent 

front pylon mount bolt and primary mount 

thrust load path failure, which could result 

in an engine separating from 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. 

INCO 718 Material Bolts Torque Checks 

(f) Perform initial and repetitive torque 

checks of INCO 718 material front pylon 

mount bolts, P/N 54T670, and replace, if 

necessary, with new bolts, using the 

Accomplishment Instructions of PW Alert 

Service Bulletin (ASB) PW4G–100–A71–9, 

Revision 1, dated November 24, 1997, as 

follows: 

(1) For front pylon mount bolts, P/N 

54T670, with fewer than 1,000 cycles-sincenew (CSN) on the effective date of this AD, 

do the following using Part (A) of the 

Accomplishment Instructions of the ASB: 

(i) Perform an initial torque check before 

accumulating 1,250 CSN or at the next engine 

removal for cause, whichever occurs sooner. 

(ii) Thereafter, perform torque checks at 

intervals of no fewer than 750 or no more 

than 1,250 cycles-in-service (CIS) since last 

torque check. 

(2) For front pylon mount bolts, P/N 

54T670, with 1,000 CSN or more but fewer 

than 5,750 CSN on the effective date of this 

AD, do the following using Part (A) of the 

Accomplishment Instructions of the ASB: 

(i) Perform an initial torque check within 

250 CIS after the effective date of this AD, or 

at the next engine removal for any cause, 

whichever occurs sooner. 

(ii) Thereafter, perform torque checks at 

intervals of no fewer than 750 or no more 

than 1,250 CIS since last torque check. 

(3) For front pylon mount bolts, P/N 

54T670, with 5,750 CSN or more on the 

effective date of this AD, do the following 

using Part (B) of the Accomplishment 

Instructions of the ASB: 


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Federal Register / Vol. 71, No. 150 / Friday, August 4, 2006 / Rules and Regulations 44187 

(i) Perform an initial torque check within 

250 CIS after the effective date of this AD, or 

before the next engine removal for any cause, 

whichever occurs sooner. 

(ii) Thereafter, perform torque checks at 

intervals of no fewer than 750 or no more 

than 1,250 CIS since last torque check. 

(4) Remove from service front pylon mount 

bolts P/N 54T670, at or before reaching the 

life limit of 11,000 CSN. 

(5) Before further flight, replace all four 

bolts using Part (A), Paragraph 1(D) of the 

Accomplishment Instructions of the ASB, if 

any of the bolts are loose or broken. 

MP159 Material Bolts Inspections 

(g) Perform initial and repetitive torque 

checks of front pylon mount bolts, P/N 

51U615, using the Accomplishment 

Instructions of PW ASB PW4G–100–A71–32, 

dated April 15, 2005, as follows: 

(1) For front pylon mount bolts with fewer 

than 2,200 CSN on the effective date of this 

AD, perform the initial torque inspection 

before accumulating 2,700 CSN, or at the 

next engine removal for any cause, 

whichever occurs sooner. 

(2) For front pylon mount bolts with 2,200 

CSN or more on the effective date of this AD, 

perform the initial torque check within the 

next 500 CIS, or at the next engine removal 

for any cause, whichever occurs sooner. 

(3) Thereafter, perform torque inspections 

at intervals not to exceed 2,700 CIS since last 

torque inspection. 

(4) Before further flight, replace all four 

bolts using Paragraph 1.E. of the 

Accomplishment Instructions of the ASB, if 

any are loose or broken. 

Primary Mount Thrust Load Path 

Inspections 

(h) Perform initial and repetitive visual 

inspections of the primary mount thrust load 

path using the Accomplishment Instructions 

of PW ASB PW4G–100–A71–18, Revision 2, 

dated January 15, 2002, as follows: 

(1) For forward engine mount assemblies 

with fewer than 1,000 CSN on the effective 

date of this AD, perform the initial visual 

inspection at the earlier of the following: 

(i) Before accumulating 1,250 CSN; or 

(ii) The next engine removal for any cause. 

(2) For forward engine mount assemblies 

with 1,000 CSN or more on the effective date 

of this AD, perform the initial visual 

inspection within 250 CIS after the effective 

date of this AD, or the next engine removal 

for any cause, whichever occurs sooner. 

(3) Thereafter, perform visual inspections 

at intervals of no fewer than 750 or no more 

than 1,250 CIS since-last-visual-inspection. 

(4) Before further flight, replace all cracked 

parts with serviceable parts and inspect the 

primary thrust load path components using 

Paragraph 4 of the Accomplishment 

Instructions of the ASB. 

Terminating Action 

(i) Replacement of the forward engine 

mount bearing housing, P/N 59T794 or P/N 

54T659 with P/N 52U420, using SB PW4G–

100–71–22, dated January 15, 2002, 

constitutes terminating action to the 

inspection requirements of paragraph (h) of 

this AD. 

Alternative Methods of Compliance 

(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. 

Related Information 

(k) None. 

Material Incorporated by Reference 

(l) You must use the Pratt & Whitney 

service information specified in Table 1 of 

this AD to perform the actions required by 

this AD. The Director of the Federal Register 

approved the incorporation by reference of 

Pratt & Whitney Alert Service Bulletin (ASB) 

PW4G–100–A71–32, dated April 15, 2005, in 

accordance with 5 U.S.C. 552(a) and 1 CFR 

part 51. The Director of the Federal Register 

previously approved the incorporation by 

reference of Pratt & Whitney ASB PW4G–

100–A71–9, Revision 1, dated November 24, 

1997, as of October 16, 2000, and, ASB 

PW4G–100–A71–18, Revision 2, dated 

January 15, 2002, and ASB PW4G–100–71–

22, dated January 15, 2002, as of February 6, 

2003. Contact Pratt & Whitney, 400 Main St., 

East Hartford, CT 06108; telephone (860) 

565–7700, fax (860) 565–1605 for the service 

information identified in this AD. You may 

review copies at the Docket Management 

Facility; U.S. Department of Transportation, 

400 Seventh Street, SW., Nassif Building, 

Room PL–401, Washington, DC 20590–0001, 

on the Internet at http://dms.dot.gov, or 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/cfr/ibrlocations.html. 

TABLE 1.—INCORPORATION BY REFERENCE

Alert Service Bulletin (ASB) or Service Bulletin (SB) No. Page Revision Date 

ASB PW4G–100–A71–9 ..................................................................................................... 1 ................... 1 ................... November 24, 1997. 

2 ................... Original ......... July 31, 1997. 

3 ................... 1 ................... November 24, 1997. 

4–7 ............... Original ......... July 31, 1997. 

8–9 ............... 1 ................... November 24, 1997. 

Total Pages: 11 ........................................................................................................... 10–11 ........... Original ......... July 31, 1997. 

ASB PW4G–100–A71–18 ................................................................................................... 1–2 ............... 2 ................... January 15, 2002. 

3 ................... 1 ................... December 9, 1999. 

4 ................... 2 ................... January 15, 2002. 

5–6 ............... Original ......... September 15, 1999. 

7 ................... 2 ................... January 15, 2002. 

Total Pages: 12 ........................................................................................................... 8–12 ............. Original ......... September 15, 1999. 

SB PW4G–100–71–22 ....................................................................................................... ALL ............... Original ......... January 15, 2002. 

Total Pages: 8 

ASB PW4G–100–A71–32 ................................................................................................... ALL ............... Original ......... April 15, 2005. 

Total Pages: 9 

Issued in Burlington, Massachusetts, on 

July 27, 2006. 

Francis A. Favara, 

Manager, Engine and Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. E6–12564 Filed 8–3–06; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 43 

Removal of References to Part 123 

From 14 CFR Part 43 

AGENCY: Federal Aviation 

Administration, DOT. 

ACTION: Final rule; technical 

amendment. 

SUMMARY: In the final rule, Certification 

and Operation Rules for Certain Large 

Airplanes, which the FAA published in 

the Federal Register on October 9, 1980, 

the FAA revoked part 123, effective 

January 1, 1983. However, references to 

part 123 remain in part 43. The purpose 

of this action is to remove those 


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