Federal Register / Vol. 70, No. 206 / Wednesday, October 26, 2005 / Rules and Regulations 61721 

(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 regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

See the ADDRESSES section for a location 

to examine the regulatory evaluation. 

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 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 Federal Aviation 

Administration (FAA) amends § 39.13 

by adding the following new 

airworthiness directive (AD): 

2005–22–05 Airbus: Amendment 39–14349. 

Docket No. FAA–2005–22170; 

Directorate Identifier 2005–NM–073–AD. 

Effective Date 

(a) This AD becomes effective November 

30, 2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Airbus Model A320–

111, –211, –212, and –231 airplanes, 

certificated in any category, that have not 

received Airbus Modification 21088 or 21999 

in production; and airplanes that have 

received Airbus Modification 21088 in 

production and have manufacturer’s serial 

numbers 91 to 113 inclusive and 140 to 189 

inclusive. 

Unsafe Condition 

(d) This AD results from fuel systems 

reviews conducted by the manufacturer. We 

are issuing this AD to prevent chafing of the 

fuel pump cables, which could result in 

electrical arcing and possible ignition of fuel 

vapors and consequent explosion of the fuel 

tank. 

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. 

Inspection and Modification of Fuel Pump 

Access Holes 

(f) Within 58 months after the effective 

date of this AD, perform the actions required 

by paragraph (f)(1) or (f)(2) of this AD, as 

applicable. 

(1) For airplanes that have not received 

Airbus Modification 21088 or 21999 in 

production: Modify the cables and access 

holes to the inner tank fuel pumps, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320–

28–1008, Revision 1, dated April 10, 1989. 

(2) For airplanes that have received Airbus 

Modification 21088 in production and have 

manufacturer’s serial numbers 91 to 113 

inclusive and 140 to 189 inclusive: Perform 

a general visual inspection for the correct 

radius of the fuel pump access holes and 

modify the access holes, as applicable, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320–

28–1054, dated August 23, 1993. Do any 

applicable repairs before further flight. 

Note 1: For the purposes of this AD, a 

general visual inspection is: ‘‘A visual 

examination of an interior or exterior area, 

installation, or assembly to detect obvious 

damage, failure, or irregularity. This level of 

inspection is made from within touching 

distance unless otherwise specified. A mirror 

may be necessary to ensure visual access to 

all surfaces in the inspection area. This level 

of inspection is made under normally 

available lighting conditions such as 

daylight, hangar lighting, flashlight, or 

droplight and may require removal or 

opening of access panels or doors. Stands, 

ladders, or platforms may be required to gain 

proximity to the area being checked.’’

No Reporting Requirement 

(g) Although Airbus Service Bulletin 

A320–28–1054, dated August 23, 1993, 

describes procedures for reporting inspection 

findings to Airbus, this AD does not require 

that report. 

Alternative Methods of Compliance 

(AMOCs) 

(h)(1) The Manager, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, has the authority to approve AMOCs 

for this AD, if requested in accordance with 

the procedures found in 14 CFR 39.19. 

(2) Before using any AMOC approved in 

accordance with § 39.19 on any airplane to 

which the AMOC applies, notify the 

appropriate principal inspector in the FAA 

Flight Standards Certificate Holding District 

Office. 

Related Information 

(i) French airworthiness directive F–2005–

031, dated February 16, 2005, also addresses 

the subject of this AD. 

Material Incorporated by Reference 

(j) You must use the service information 

identified in Table 1 of this AD to perform 

the actions that are required by this AD, 

unless the AD specifies otherwise. Airbus 

Service Bulletin A320–28–1008, Revision 1, 

dated April 10, 1989, contains the following 

effective pages: 

Page No. 

Revision level 

shown on 

page 

Date 

shown on 

page 

1, 2, 7–9 ....... 1 ................... April 10, 

1989. 

3–6 ............... Original ........ February 9, 

1989. 

The Director of the Federal Register 

approved the incorporation by reference of 

these documents in accordance with 5 U.S.C. 

552(a) and 1 CFR part 51. Contact Airbus, 1 

Rond Point Maurice Bellonte, 31707 Blagnac 

Cedex, France, for a copy of this service 

information. You may review copies at the 

Docket Management Facility, U.S. 

Department of Transportation, 400 Seventh 

Street SW., room PL–401, Nassif Building, 

Washington, DC; 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 the NARA, call (202) 741–6030, 

or go to http://www.archives.gov/ 

federal_register/code_of_federal_regulations/ 

ibr_locations.html. 

Airbus service 

bulletin Revision level Date 

A320–28–

1008.

1 ................... April 10, 

1989. 

A320–28–

1054.

Original ........ August 23, 

1993. 

Issued in Renton, Washington, on October 

18, 2005. 

Kevin M. Mullin, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 05–21312 Filed 10–25–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–22757; Directorate 

Identifier 2005–SW–32–AD; Amendment 39–

14345; AD 2005–22–01] 

RIN 2120–AA64 

Airworthiness Directives; Sikorsky 

Aircraft Corporation Model S–76A, B, 

and C Helicopters 

AGENCY: Federal Aviation 

Administration, DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: This amendment adopts a 

new airworthiness directive (AD) for the 

Sikorsky Aircraft Corporation (Sikorsky) 

Model S–76A, B, and C helicopters. 

This action requires certain inspections 

of the main rotor lower bifilar arm 

assembly in the attachment area around 

the lower bifilar lugs for a crack. If a 

61722 Federal Register / Vol. 70, No. 206 / Wednesday, October 26, 2005 / Rules and Regulations 

crack is found on any bifilar lug, this 

AD requires replacing the bifilar arm 

assembly with an airworthy bifilar arm 

assembly. If no crack is found, this AD 

requires a one-time test for the required 

torque on the lug nuts and, if necessary, 

applying the required torque and 

conducting the torque stabilization tests. 

This amendment is prompted by four 

reports of cracked bifilars. The actions 

specified in this AD are intended to 

prevent failure of a bifilar lug, damage 

to the main rotor control system, and 

subsequent loss of control of the 

helicopter. 

DATES: Effective November 10, 2005. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of November 

10, 2005. 

Comments for inclusion in the Rules 

Docket must be received on or before 

December 27, 2005. 

ADDRESSES: Use one of the following 

addresses to submit comments on this 

AD: 

• DOT Docket Web site: Go to 

http://dms.dot.gov and follow the 

instructions for sending your comments 

electronically; 

• Government-wide rulemaking Web 

site: Go to http://www.regulations.gov 

and follow the instructions for sending 

your comments electronically; 

• Mail: Docket Management Facility; 

U.S. Department of Transportation, 400 

Seventh Street SW., Nassif Building, 

Room PL–401, Washington, DC 20590; 

• Fax: (202) 493–2251; or 

• Hand Delivery: Room PL–401 on 

the plaza level of the Nassif Building, 

400 Seventh Street SW., Washington, 

DC, between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

You may get the service information 

identified in this AD from Sikorsky 

Aircraft Corporation, Attn: Manager, 

Commercial Tech Support, 6900 Main 

Street, Stratford, Connecticut 06614, 

phone (203) 386–3001, fax (203) 386–

5983. 

Examining the Docket 

You may examine the docket that 

contains the AD, any comments, and 

other information on the Internet at 

http://dms.dot.gov, or in person at the 

Docket Management System (DMS) 

Docket Offices between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. The Docket Office 

(telephone (800) 647–5227) is located on 

the plaza level of the Department of 

Transportation Nassif Building at the 

street address stated in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after the DMS 

receives them. 

FOR FURTHER INFORMATION CONTACT: 

Tracy Murphy, Aviation Safety 

Engineer, Boston Aircraft Certification 

Office, 12 New England Executive Park, 

Burlington, MA 01803, telephone (781) 

238–7172, fax (781) 238–7170. 

SUPPLEMENTARY INFORMATION: This 

amendment adopts a new AD for 

Sikorsky Model S–76A, B, and C 

helicopters. This action requires certain 

inspections of the main rotor lower 

bifilar arm assembly around the lower 

bifilar lugs for a crack. If a crack is 

found on any bifilar lug, this AD 

requires replacing the bifilar arm 

assembly with an airworthy bifilar arm 

assembly. If no crack is found, this AD 

requires a one-time test for the required 

torque on the lug nuts and, if necessary, 

applying the required torque and 

conducting the torque stabilization tests. 

This amendment is prompted by four 

reports of cracked bifilars. The actions 

specified in this AD are intended to 

prevent failure of a bifilar lug, damage 

to the main rotor system, and 

subsequent loss of control of the 

helicopter. 

Sikorsky issued Alert Service Bulletin 

No. 76–65–62, dated December 14, 2004 

(ASB), after receiving two reports of 

cracks in the lug areas of helicopters. 

Sikorsky states that cracked lugs were 

found despite the lower support lug 

joining being torqued and stabilized. For 

a bifilar with more than 1500 hours, the 

ASB specifies performing, within 100 

flight hours from the issue date of the 

ASB, a one-time inspection of the lower 

bifilar support lugs for cracks in the lug 

attachment areas. These are considered 

interim actions until terminating action 

can be taken. Sikorsky has designed and 

is currently testing a new main rotor 

hub pilot fitting (pilot fitting). 

Since Sikorsky issued the ASB, the 

FAA has received two more reports for 

a total of four reports of cracked bifilars. 

The additional reports indicate that 

cracks have become more severe. 

Therefore, this AD will require a repeat 

inspection of the arm assembly in 

addition to the inspections in the ASB. 

Also, this AD is effective for helicopters 

with a pilot fitting, part number (P/N) 

76103–08003–101, which is different 

from what the ASB specifies. 

Investigation has shown the root cause 

of the failure is not the bifilar itself but 

the mating part that attaches the bifilar 

to the main rotor hub, called the pilot 

fitting. This fitting is transferring the 

load too abruptly into the bifilar. The 

ongoing fatigue testing is with the 

production bifilar and the redesigned 

pilot fitting. If the tests are successful, 

terminating action likely will include 

installing the new pilot fitting. The 

frequency of reports and the severity of 

the failures prompted this AD. In the 

most recent report, six of the six lugs 

had separated from the bifilar. 

This unsafe condition is likely to exist 

or develop on other helicopters of these 

same type designs. Therefore, this AD is 

being issued to prevent failure of a 

bifilar lug, damage to the main rotor 

system, and subsequent loss of control 

of the helicopter. This AD requires the 

following for helicopters with a pilot 

fitting, part number (P/N) 76103–08003–

101, with 1500 or more hours time-inservice (TIS): 

• Within 50 hours TIS, unless 

accomplished previously, and thereafter 

at intervals not to exceed 50 hours TIS, 

inspect the bifilar arm assembly for a 

crack in the lug attachment area. 

• If you find a crack on any bifilar 

arm assembly lug, before further flight, 

replace the bifilar arm assembly with an 

airworthy bifilar arm assembly. 

• If no crack is found at the initial 

inspection, perform a one-time torque 

test. The torque test is not required at 

the recurring inspection intervals of the 

bifilar arm assembly. 

Accomplish the actions by following 

the specified portions of the ASB 

described previously. 

The short compliance time involved 

is required because the previously 

described critical unsafe condition can 

adversely affect the structural integrity 

of the helicopter. This AD requires the 

affected helicopters to be inspected and 

undergo a torque test within 50 hours 

TIS. If you find a crack in the bifilar lug 

attachment area, this AD requires 

replacing any unairworthy bifilar arm 

assembly with an airworthy bifilar arm 

assembly before further flight. 

Therefore, this AD must be issued 

immediately. 

Since a situation exists that requires 

the immediate adoption of this 

regulation, it is found that notice and 

opportunity for prior public comment 

hereon are impracticable, and that good 

cause exists for making this amendment 

effective in less than 30 days. 

We estimate that this AD will: 

• Affect 216 helicopters, 

• Take about 4 work hours for each 

inspection (including the torque 

stabilization tests), assuming 6 

inspections per year, and 4 hours to 

replace the bifilars, assuming a total of 

2 bifilar arm assemblies need replacing, 

and 

• Cost about $19,727 for a bifilar arm 

assembly. 

Based on these figures, we estimate 

the total cost impact of the AD on U.S. 

operators to be $376,934. 

Federal Register / Vol. 70, No. 206 / Wednesday, October 26, 2005 / Rules and Regulations 61723 

Comments Invited 

This AD is a final rule that involves 

requirements that affect flight safety and 

was not preceded by notice and an 

opportunity for public comment; 

however, we invite you to submit any 

written data, views, or arguments 

regarding this AD. Send your comments 

to an address listed under ADDRESSES. 

Include ‘‘Docket No. FAA–2005–22757; 

Directorate Identifier 2005–SW–32–AD’’

at the beginning of your comments. We 

specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

the AD. We will consider all comments 

received by the closing date and may 

amend the AD in light of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

dms.dot.gov, including any personal 

information you provide. We will also 

post a report summarizing each 

substantive verbal contact with FAA 

personnel concerning this AD. Using the 

search function of our docket web site, 

you can find and read the comments to 

any of our dockets, including the name 

of the individual who sent the 

comment. You may review the DOT’s 

complete Privacy Act Statement in the 

Federal Register published on April 11, 

2000 (65 FR 19477–78), or you may visit 

http://dms.dot.gov. 

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 an economic evaluation 

of the estimated costs to comply with 

this AD. See the DMS to examine the 

economic evaluation. 

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. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

■ Accordingly, pursuant to the authority 

delegated to me by the Administrator, 

the Federal Aviation Administration 

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. Section 39.13 is amended by adding 

a new airworthiness directive to read as 

follows: 

2005–22–01 Sikorsky Aircraft Corporation: 

Amendment 39–14345. Docket No. 

FAA–2005–22757; Directorate Identifier 

2005–SW–32–AD. 

Applicability: Model S–76A, B, and C, with 

a main rotor hub pilot fitting (pilot fitting), 

part number (P/N) 76103–08003–101, with 

1500 or more hours time-in-service (TIS), 

installed, certificated in any category. 

Compliance: Required as indicated. 

To prevent failure of a bifilar lug, damage 

to the main rotor system, and subsequent loss 

of control of the helicopter, accomplish the 

following: 

(a) Within 50 hours TIS, and thereafter at 

intervals not to exceed 50 hours TIS, inspect 

the lower bifilar arm assembly for a crack in 

the lug attachment area. Conduct the 

inspection of the lower bifilar arm assembly 

by following the Accomplishment 

Instructions, paragraph 3.A.(1) through 

3.A.(6), of Sikorsky Alert Service Bulletin No. 

76–65–62, dated December 14, 2004 (ASB). 

(1) If you find a crack on any bifilar arm 

assembly lug, before further flight, replace 

the bifilar arm assembly with an airworthy 

bifilar arm assembly. 

(2) If no crack is found at the initial 

inspection, perform a one-time torque test. 

Perform the torque test and the additional 

torque procedures as stated in the 

Accomplishment Instructions, paragraph 

3.B.(1) through 3.B.(3) of the ASB. The torque 

test is not required at the recurring 

inspection intervals of the lower bifilar arm 

assembly. 

(b) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Contact the Boston Aircraft 

Certification Office, FAA, for information 

about previously approved alternative 

methods of compliance. 

(c) Inspect the lower bifilar arm assembly 

and perform the torque test by following the 

specified portions of Sikorsky Alert Service 

Bulletin No. 76–65–62, dated December 14, 

2004. The Director of the Federal Register 

approved this incorporation by reference in 

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

part 51. Copies may be obtained from 

Sikorsky Aircraft Corporation, Attn: Manager, 

Commercial Tech Support, 6900 Main Street, 

Stratford, Connecticut 06614, phone (203) 

386–3001, fax (203) 386–5983. Copies may be 

inspected 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. 

(d) This amendment becomes effective on 

November 10, 2005. 

Issued in Fort Worth, Texas, on October 17, 

2005. 

David A. Downey, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 05–21256 Filed 10–25–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–22018; Directorate 

Identifier 2005–CE–41–AD; Amendment 39–

14348; AD 2005–22–04] 

RIN 2120–AA64 

Airworthiness Directives; Pilatus 

Aircraft Ltd. Models PC–12 and PC–12/ 

45 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA adopts a new 

airworthiness directive (AD) for certain 

Pilatus Aircraft Ltd. (Pilatus) Models 

PC–12 and PC–12/45 airplanes. This AD 

requires you to determine (maintenance 

records check and/or inspection) 

whether certain nose landing gear 

(NLG), main landing gear (MLG), and 

MLG shock absorber assemblies with a 

serial number beginning with ‘‘AM’’ are