58826 Federal Register / Vol. 69, No. 190 / Friday, October 1, 2004 / Rules and Regulations 

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 the regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

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.

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety.

Adoption of the Amendment

■ Under the authority delegated to me by 

the Administrator, the FAA amends part 

39 of the Federal Aviation Regulations 

(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 Federal Aviation 

Administration (FAA) amends § 39.13 by 

adding the following new airworthiness 

directive (AD):

2004–20–04 Pratt & Whitney Canada:

Amendment 39–13809. Docket No. 

FAA–2004–19170; Directorate Identifier 

2004–NE–18–AD. 

Effective Date 

(a) This AD becomes effective October 18, 

2004. 

Affected ADs 

(b) None.

Applicability 

(c) This AD applies to Pratt & Whitney 

Canada (PWC) PT6B–36A and PT6B–36B 

turboshaft engines with compressor rear 

hubs, part number (P/N) 3018111 installed. 

These engines are installed on, but not 

limited to, Sikorsky S–76B helicopters. 

Unsafe Condition 

(d) This AD results from results from the 

discovery of a compressor rear hub, P/N 

3018111, that exceeded the published life 

limit. This occurred because the operator 

used an incorrect life limit calculation 

contained in a PWC Service Bulletin. We are 

issuing this AD to prevent uncontained 

failure of the compressor rear hub and 

damage to the helicopter. 

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 30 days or at the next engine 

shop visit, whichever occurs first after the 

effective date of this AD, do the following: 

(1) Using the Flight Count Factor of 3, 

review and correct the critical part record for 

compressor rear hubs, P/N 3018111. Use 

paragraph 3 of the Accomplishment 

Instructions of PWC Service Bulletin (SB) No. 

PT6B–72–11002, Revision 8, dated June 11, 

2003, to do this. 

(2) Remove the compressor rear hub from 

service before further flight, if its life limit is 

found to be at or higher than the published 

life limit in PWC SB No. PT6B–72–11002, 

Revision 8, dated June 11, 2003. 

Alternative Methods of Compliance 

(g) 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. 

Special Flight Permits 

(h) Under 14 CFR part 39.23, we are 

limiting the special flight permits for this AD 

by allowing the engine to operate an 

additional 25 cycles-in-service or 25 

operating hours, whichever occurs first, for 

moving the helicopter to a location where the 

requirements of this AD can be done. 

Material Incorporated by Reference 

(i) You must use Pratt & Whitney Canada 

Service Bulletin No. PT6B–72–11002, 

Revision 8, dated June 11, 2003, to perform 

the reviews and corrections required by this 

AD. The Director of the Federal Register 

approved the incorporation by reference of 

this service bulletin in accordance with 5 

U.S.C. 552(a) and 1 CFR part 51. You can get 

a copy from Pratt & Whitney Canada, 1000 

Marie-Victorin, Longueuil, Quebec, Canada 

J4G1A1. 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 20590–001, 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/code_of_federal_regulations/

ibr_locations.html.

Related Information 

(j) Transport Canada airworthiness 

directive CF–2003–16, dated June 27, 2003, 

also addresses the subject of this AD.

Issued in Burlington, Massachusetts, on 

September 24, 2004. 

Francis A. Favara, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service.

[FR Doc. 04–21913 Filed 9–30–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2003–NE–35–AD; Amendment 

39–13806; AD 2004–20–01] 

RIN 2120–AA64 

Airworthiness Directives; Pratt & 

Whitney Canada Models PW123, 

PW123B, PW123C, PW123D, PW123E, 

PW123AF, PW124B, PW125B, PW126A, 

PW127, PW127E, PW127F, and 

PW127G Turboprop Engines

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Final rule.

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for Pratt & 

Whitney Canada (PWC) models PW123, 

PW123B, PW123C, PW123D, PW123E, 

PW123AF, PW124B, PW125B, PW126A, 

PW127, PW127E, PW127F, and 

PW127G turboprop engines. This AD 

requires initial and repetitive gap 

inspections of the bypass valve cover, 

on certain part number (P/N) 

mechanical fuel controls (MFCs), and 

replacement of those MFCs as 

mandatory terminating action to the 

repetitive inspections. This AD is 

prompted by sixteen reports of loss of 

engine throttle response and overspeed, 

eight of which resulted in in-flight 

shutdown. We are issuing this AD to 

prevent loss of throttle response and 

overspeed, resulting in engine in-flight 

shutdown.

DATES: This AD becomes effective 

November 5, 2004. The Director of the 

Federal Register approved the 

incorporation by reference of certain 

publications listed in the regulations as 

of November 5, 2004.

ADDRESSES: You can get the service 

information identified in this AD from 

Honeywell Engines & Systems, 

Technical Publications Department, 111 

South 34th Street, Phoenix, Arizona 

85034; telephone (602) 365–5535; fax 

(602) 365–5577. 

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 

Federal Register / Vol. 69, No. 190 / Friday, October 1, 2004 / Rules and Regulations 58827

the FAA, New England Region, Office of 

the Regional Counsel, 12 New England 

Executive Park, Burlington, MA; 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/

code_of_federal_regulations/

ibr_locations.html.

FOR FURTHER INFORMATION CONTACT: Ian 

Dargin, Aerospace Engineer, Engine 

Certification Office, FAA, Engine and 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803–

5299; telephone (781) 238–7178; fax 

(781) 238–7199.

SUPPLEMENTARY INFORMATION: The FAA 

proposed to amend 14 CFR part 39 with 

a proposed AD. The proposed AD 

applies to PWC models PW123, 

PW123B, PW123C, PW123D, PW123E, 

PW123AF, PW124B, PW125B, PW126A, 

PW127, PW127E, PW127F, and 

PW127G turboprop engines. We 

published the proposed AD in the 

Federal Register on December 10, 2003 

(68 FR 68802). That action proposed to 

require initial and repetitive gap 

inspections of the bypass valve cover, 

on certain part number (P/N) 

mechanical fuel controls (MFCs), and 

replacement of those MFCs as 

mandatory terminating action to the 

repetitive inspections. 

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 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. 

Conclusion 

We have carefully reviewed the 

available data and determined that air 

safety and the public interest require 

adopting the AD as proposed. 

Costs of Compliance 

There are about 2,800 PWC models 

PW123, PW123B, PW123C, PW123D, 

PW123E, PW123AF, PW124B, PW125B, 

PW126A, PW127, PW127E, PW127F, 

and PW127G turboprop engines of the 

affected design in the worldwide fleet. 

We estimate that 473 engines installed 

on airplanes of U.S. registry will be 

affected by this AD. We also estimate 

that it will take about 0.1 work hour per 

engine to perform the inspection, about 

1 work hour per engine to replace the 

MFC during maintenance, and that the 

average labor rate is $65 per work hour. 

Required parts will cost about $72,000 

per engine. Based on these figures, we 

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

operators to be $34,089,819. The 

manufacturer has stated that it may 

provide the new design MFCs at no cost 

to operators, and that if the MFC is 

replaced at shop visit, no additional 

labor costs will be incurred. 

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. 2003–NE–35–

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 adding 

the following new airworthiness 

directive (AD):

2004–20–01 Pratt & Whitney Canada:

Amendment 39–13806. Docket No. 

2003–NE–35–AD. 

Effective Date 

(a) This AD becomes effective November 5, 

2004. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Pratt & Whitney 

Canada (PWC) models PW123, PW123B, 

PW123C, PW123D, PW123E, PW123AF, 

PW124B, PW125B, PW126A, PW127, 

PW127E, PW127F, and PW127G turboprop 

engines, with mechanical fuel controls 

(MFCs), part numbers (P/Ns) 3244841–21, 

3244853–17, 3244855–15, 3244857–14, 

3244858–23, 3244871–5, 3244873–4, and 

3244874–4, installed. These engines are 

installed on, but not limited to, Aerospatiale 

ATR 42 and ATR 72, BAE Systems 

(Operations) Limited ATP, Bombardier Inc. 

DHC–8–200 series, DHC–8–300 series, CL–

215T, and CL–415, Construcciones 

Aeronauticas, S.A. (CASA) C–295, Fokker 

Aircraft B.V. F27 Mark 050, and Mark 060 

airplanes. 

Unsafe Condition 

(d) This AD is prompted by sixteen reports 

of loss of engine throttle response and 

overspeed, eight of which resulted in inflight shutdown. We are issuing this AD to 

prevent loss of throttle response and 

overspeed, resulting in engine in-flight 

shutdown. 

Compliance 

(e) Compliance with this AD is required as 

indicated, unless already done. 

Initial Gap Inspection 

(f) Within 500 hours time-in-service (TIS) 

after the effective date of the AD, perform a 

gap inspection between the MFC bypass 

valve cover and the MFC main body, and 

disposition the MFC. Follow paragraphs 5.0 

through 5.3 of Honeywell Service 

Information Bulletin (SIB) No. 82, dated 

September 14, 2001, to do the inspection and 

MFC disposition. 

Repetitive Gap Inspections 

(g) At intervals of 1,500 hours TIS from the 

last gap inspection, perform repetitive gap 

inspections between the MFC bypass valve 

cover and the MFC main body and 

disposition the MFC. Follow paragraphs 5.0 

through 5.3 of Honeywell SIB No. 82, dated 

September 14, 2001, to do the inspection and 

MFC disposition. 

Mandatory Terminating Action 

(h) Within 4,500 hours TIS or 24 months 

from the effective date of this AD, whichever 

occurs first, replace the MFC with an MFC 

not having a P/N listed in paragraph (c) of 

this AD. 

(i) Replacement of the MFC with an MFC 

whose P/N is not listed in paragraph (c) of 

this AD constitutes mandatory terminating 

action to the repetitive inspection 

requirements specified in paragraph (g) of 

this AD. Information on new design 

replacement MFCs can be found in PWC 

Service Bulletin No. PW100–72–21562, 

Revision 2, dated December 7, 2000. 

58828 Federal Register / Vol. 69, No. 190 / Friday, October 1, 2004 / Rules and Regulations 

Material Incorporated by Reference 

(j) You must use Honeywell Service 

Information Bulletin No. 82, dated September 

14, 2001, to perform the inspections required 

by this AD. The Director of the Federal 

Register approved the incorporation by 

reference of this service bulletin in 

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

part 51. You can get a copy from Honeywell 

Engines & Systems, Technical Publications 

Department, 111 South 34th Street, Phoenix, 

Arizona 85034; telephone (602) 365–5535; 

fax (602) 365–5577. You can review copies at 

FAA, New England Region, Office of the 

Regional Counsel, 12 New England Executive 

Park, Burlington, MA, 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/code_of_federal_regulations/

ibr_locations.html.

Related Information 

(k) None.

Issued in Burlington, Massachusetts, on 

September 24, 2004. 

Francis A. Favara, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service.

[FR Doc. 04–21911 Filed 9–30–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2001–NM–254–AD; Amendment 

39–13805; AD 2004–19–11] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A320 Series Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes 

an existing airworthiness directive (AD), 

applicable to certain Airbus Model 

A320 series airplanes, that currently 

requires modification of the rear spar 

web of the wing, cold expansion of 

certain attachment holes for the forward 

pintle fitting and certain holes at the 

actuating cylinder anchorage of the 

main landing gear (MLG), repetitive 

inspections for fatigue cracking in 

certain areas of the rear spar of the wing, 

and corrective action if necessary. That 

AD also provides for optional 

terminating action for the requirements 

of the AD. This amendment revises 

certain compliance times for the 

inspection. The actions specified by this 

AD are intended to detect and correct 

fatigue cracking, which may lead to 

reduced structural integrity of the wing 

and the MLG. This action is intended to 

address the identified unsafe condition.

DATES: Effective November 5, 2004. 

The incorporation by reference of a 

certain publication, as listed in the 

regulations, is approved by the Director 

of the Federal Register as of November 

5, 2004. 

The incorporation by reference of 

certain other publications, as listed in 

the regulations, was approved 

previously by the Director of the Federal 

Register as of June 30, 2000 (65 FR 

34069, May 26, 2000); February 14, 1994 

(59 FR 1903, January 13, 1994); and June 

11, 1993 (58 FR 27923, May 12, 1993).

ADDRESSES: The service information 

referenced in this AD may be obtained 

from Airbus, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France. 

This information may be examined at 

the Federal Aviation Administration 

(FAA), Transport Airplane Directorate, 

Rules Docket, 1601 Lind Avenue, SW., 

Renton, Washington; 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/

code_of_federal_regulations/

ibr_locations.html.

FOR FURTHER INFORMATION CONTACT: Tim 

Dulin, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–2141; 

fax (425) 227–1149.

SUPPLEMENTARY INFORMATION: A 

proposal to amend part 39 of the Federal 

Aviation Regulations (14 CFR part 39) 

by superseding AD 2000–10–15, 

amendment 39–11739 (65 FR 34069, 

May 26, 2000), which is applicable to 

certain Airbus Model A320 series 

airplanes, was published in the Federal 

Register on February 13, 2004 (69 FR 

7176). The action proposed to retain the 

requirements of AD 2000–10–15 

(modification of the rear spar web of the 

wing, cold expansion of certain 

attachment holes for the forward pintle 

fitting and certain holes at the actuating 

cylinder anchorage of the main landing 

gear (MLG), and repetitive inspections 

for fatigue cracking in certain areas of 

the rear spar of the wing; and corrective 

action if necessary; with optional 

terminating action for those 

requirements). The notice of proposed 

rulemaking (NPRM) proposed to revise 

the threshold and repetitive intervals for 

the inspection. 

Comments 

Interested persons have been afforded 

an opportunity to participate in the 

making of this amendment. Due 

consideration has been given to the 

comments received. 

Support for the Proposed AD 

One commenter supports the AD as 

proposed. 

Request To Revise Certain Compliance 

Time 

One commenter, an airline operator, 

suggests that the grace period (60 days) 

specified in paragraph (c)(1) of the 

proposed AD is overly restrictive. The 

operator requests that the grace period 

be changed to correspond to the next Ccheck (18 months for this operator). 

This recommended grace period would 

provide sufficient time for operators to 

do the optional terminating 

modification specified in the proposed 

AD. The operator reports that the 

modification (which has been done on 

80 percent of its fleet to date) has 

revealed only one cracked fastener hole, 

representing 0.05 percent of all fastener 

holes inspected. The operator asserts 

that its proposed grace period would 

still allow for the safe continued 

airworthiness of the affected airplanes. 

The FAA agrees with the commenter’s 

request and rationale. We agree that the 

proposed 60-day grace period was 

unnecessarily restrictive. The 

commenter’s proposed grace period 

approximates the grace periods 

mandated by the parallel French 

airworthiness directive. We have 

accordingly revised the grace period in 

paragraph (c)(1) of this final rule. 

Additional Change to the Final Rule 

Because the language in Note 2 of the 

proposed AD is regulatory in nature, 

that note has been redesignated as 

paragraph (d) of this final rule. 

Conclusion 

After careful review of the available 

data, including the comments noted 

above, the FAA has determined that air 

safety and the public interest require the 

adoption of the rule with the changes 

previously described. The FAA has 

determined that these changes will 

neither increase the economic burden 

on any operator nor increase the scope 

of the AD.

Cost Impact 

This AD will affect about 126 

airplanes of U.S. registry. The following 

table provides the cost estimates of the 

actions currently required by AD 2000–

10–15: