20530 Federal Register / Vol. 71, No. 77 / Friday, April 21, 2006 / Rules and Regulations 

Exception to Service Bulletin 

(i) Where the service bulletin specifies to 

contact Boeing for appropriate action, do the 

corrective action using a method approved in 

accordance with paragraph (l) of this AD. 

Credit for Certain Corrective Actions 

(j) Reworking the lugs on the bulkhead 

fitting of the rear engine mount as specified 

in paragraphs (b)(2), (e), and (f) of AD 2001–

15–15, amendment 39–12349, is acceptable 

for compliance with accomplishing the 

corrective action specified in ‘‘Part 3—Rear 

Engine Mount Bulkhead Inspection and Lug 

Overhaul and Upper Fitting Overhaul and 

Bolt Replacement’’ of the service bulletin. 

New Requirements of This AD 

Terminating Action—Repetitive Replacement 

or Overhaul of All Thrust Links 

(k) At the applicable compliance times 

specified in Table 1 of this AD: Repetitively 

replace the thrust link of the rear engine 

mount of struts 1, 2, 3, and 4 with a new or 

overhauled thrust link, in accordance with 

Part 2 of the service bulletin; except as 

provided by paragraph (i) of this AD. During 

any replacement required by this paragraph, 

an existing thrust link may be replaced with 

a new or overhauled thrust link having P/N 

65B90360–1, –4 or –7, provided that the 

applicable repetitive interval specified in 

Table 1 of this AD is complied with. If a 

fractured thrust link is found during any 

replacement or overhaul done in accordance 

with this paragraph: Before further flight, do 

the corrective actions specified in paragraph 

(h)(2) of this AD. Repetitive replacement of 

all thrust links having P/N 65B90360–1 or –4 

terminates the repetitive inspections required 

by paragraph (g) of this AD. Accomplishing 

the repetitive replacement or overhaul of a 

thrust link required by paragraph (h) of this 

AD constitutes compliance with the 

requirements of this paragraph for that thrust 

link only. 

TABLE 1.—COMPLIANCE TIMES

For thrust link P/N— Initial replacement— Repetitive interval—

65B90360–1 or –4 ............................................. Within 36 months after the effective date of 

this AD.

Thereafter at intervals not to exceed 6,000 

flight cycles. 

65B90360–7 ...................................................... Within 12,000 flight cycles after the new thrust 

link has been installed.

Thereafter at intervals not to exceed 12,000 

flight cycles. 

Alternative Methods of Compliance 

(AMOCs) 

(l)(1) The Manager, Seattle Aircraft 

Certification Office (ACO), 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. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD, if it is approved by an 

Authorized Representative for the Boeing 

Commercial Airplanes Delegation Option 

Authorization Organization who has been 

authorized by the Manager, Seattle ACO, to 

make those findings. For a repair method to 

be approved, the repair must meet the 

certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) The actions identified in paragraphs (g) 

and (k) of this AD are approved as an AMOC 

to paragraphs (c) and (d) of AD 2004–07–22, 

amendment 39–13566, for the inspections of 

structural significant item S–2, for the thrust 

links only, of Boeing Supplemental 

Structural Inspection Document D6–35022, 

Revision G, dated December 2000. All 

provisions of AD 2004–07–22 that are not 

specifically referenced in this paragraph, 

including the initial inspection threshold 

required by paragraph (d) of AD 2004–07–22, 

remain fully applicable and must be 

complied with. 

(5) AMOCs approved previously in 

accordance with AD 2005–19–06, 

amendment 39–14271, are approved as 

AMOCs for the corresponding provisions of 

this AD. 

Material Incorporated by Reference 

(m) You must use Boeing Alert Service 

Bulletin 747–71A2309, dated August 18, 

2005, to perform the actions that are required 

by this AD, unless the AD specifies 

otherwise. On September 30, 2005 (70 FR 

54474, September 15, 2005), the Director of 

the Federal Register approved the 

incorporation by reference of Boeing Alert 

Service Bulletin 747–71A2309, dated August 

18, 2005. Contact Boeing Commercial 

Airplanes, P.O. Box 3707, Seattle, 

Washington 98124–2207, 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. 

Issued in Renton, Washington, on April 13, 

2006. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 06–3796 Filed 4–20–06; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–24364; Directorate 

Identifier 2004–NM–272–AD; Amendment 

39–14534; AD 2006–07–07] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A300 B4–600, B4–600R, and F4–600R 

Series Airplanes, and Model C4–605R 

Variant F Airplanes (Collectively Called 

A300–600 Series Airplanes) 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; correction. 

SUMMARY: The FAA is correcting a 

typographical error in an existing 

airworthiness directive (AD) that was 

published in the Federal Register on 

March 31, 2006 (71 FR 16206). The error 

resulted in an incorrect Docket No. This 

AD applies to certain Airbus Model 

A300–600 series airplanes. This AD 

requires modifying nine bolt holes in 

the vertical flange to prevent cracking 

before the inspection threshold of AD 

98–18–02. 

DATES: Effective April 17, 2006. 

ADDRESSES: The AD docket contains the 

proposed AD, comments, and any final 

disposition. You may examine the AD 

docket on the Internet at http:// 

dms.dot.gov, or in person at the Docket 

Management Facility office between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The 

Docket Management Facility office 


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Federal Register / Vol. 71, No. 77 / Friday, April 21, 2006 / Rules and Regulations 20531 

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

the plaza level of the Nassif Building at 

the U.S. Department of Transportation, 

400 Seventh Street, SW., room PL–401, 

Washington, DC. This docket number is 

FAA–2006–24364; the directorate 

identifier for this docket is 2004–NM–

272–AD. 

FOR FURTHER INFORMATION CONTACT: Tim 

Backman, Aerospace Engineer, ANM–

116, International Branch, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–2797; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: On March 

15, 2006, the FAA issued AD 2006–07–

07, amendment 39–14534 (71 FR 16206, 

March 31, 2006), for certain Airbus 

Model A300–600 series airplanes. The 

AD requires modifying nine bolt holes 

in the vertical flange to prevent cracking 

before the inspection threshold of AD 

98–18–02. 

As published, the AD lists the Docket 

No. as FAA–2006–24124. The correct 

Docket No. is FAA–2006–24364. 

No other part of the regulatory 

information has been changed; 

therefore, the final rule is not 

republished in the Federal Register. 

The effective date of this AD remains 

April 17, 2006. 

In the Federal Register of March 31, 

2006, on page 16206, in the first 

column; on page 16207, in the third 

column; and on page 16208 in the 

second column; the Docket No. of AD 

2006–07–07 is corrected to read as 

follows: FAA–2006–24364. 

Issued in Renton, Washington, on April 13, 

2006. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 06–3797 Filed 4–20–06; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–24117; Directorate 

Identifier 2006–NE–07–AD; Amendment 39–

14570; AD 2006–08–13] 

RIN 2120–AA64 

Airworthiness Directives; Pratt & 

Whitney Canada (PWC) PW535A 

Turboshaft Engines 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for Pratt & 

Whitney Canada (PWC) PW535A 

turboshaft engines with serial numbers 

(SNs) lower than DC0241, and with 

hydromechanical fuel control (HFC) 

part number (P/N) 819735–4, 819735–5, 

or 819735–6 installed. This AD requires 

inspection and verification of the proper 

adjustment of the ratio unit setscrew 

adjustment of installed HFC units. This 

AD results from incidents of PW535A 

turboshaft engines experiencing lack of 

response to the power lever input 

during attempted engine acceleration, 

due to an incorrect adjustment of the 

HFC ratio unit setscrew. We are issuing 

this AD to prevent lack of engine 

response to power lever input, which 

could cause a single or dual engine inflight shutdown event. 

DATES: Effective May 8, 2006. The 

Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the 

regulations as of May 8, 2006. We must 

receive any comments on this AD by 

June 20, 2006. 

ADDRESSES: Use one of the following 

addresses to comment 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–

0001. 

• Fax: (202) 493–2251. 

• 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. 

Contact Pratt & Whitney Canada, 1000 

Marie-Victorin, Longueuil, Quebec, 

Canada, J4G 1A1; telephone 800–268–

8000; fax 450–647–2888, for the service 

information identified in this AD. 

FOR FURTHER INFORMATION CONTACT: Ian 

Dargin, Aerospace Engineer, Engine 

Certification Office, FAA, Engine and 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

telephone (781) 238–7178; fax (781) 

238–7199. 

SUPPLEMENTARY INFORMATION: Transport 

Canada, which is the airworthiness 

authority for Canada, recently notified 

us that an unsafe condition may exist on 

PWC PW535A turboshaft engines with 

SNs lower than DC0241. Transport 

Canada advises that they received 

reports of incidents of PW535A 

turboshaft engines experiencing lack of 

response to the power lever input 

during engine acceleration, due to an 

incorrect adjustment of the HFC ratio 

unit setscrew. Two events resulted in 

engine in-flight shutdowns. 

Relevant Service Information 

We have reviewed and approved the 

technical contents of PWC Alert Service 

Bulletin (ASB) No. PW500–72–A30257, 

Revision 1, dated December 3, 2004, 

that describes procedures for inspecting 

and verifying proper adjustment of the 

ratio unit setscrew of installed HFC 

units. Transport Canada classified this 

ASB as mandatory and issued AD CF–

2004–28 in order to ensure the 

airworthiness of these PWC engines in 

Canada. 

Bilateral Airworthiness Agreement 

This PW535A turboshaft engine 

model is manufactured in Canada and is 

type certificated for operation in the 

United States under the provisions of 

section 21.29 of the Federal Aviation 

Regulations (14 CFR 21.29) and the 

applicable bilateral airworthiness 

agreement. Under this bilateral 

airworthiness agreement, Transport 

Canada kept the FAA informed of the 

situation described above. We have 

examined the findings of Transport 

Canada, reviewed all available 

information, and determined that AD 

action is necessary for products of this 

type design that are certificated for 

operation in the United States. 

FAA’s Determination and Requirements 

of This AD 

The unsafe condition described 

previously is likely to exist or develop 

on other PW535A turboshaft engines of 

the same type design. We are issuing 

this AD to prevent lack of engine 

response to power lever input, which 

could cause a single or dual engine inflight shutdown event. This AD requires 

inspection and verification of the proper 

adjustment of the ratio unit setscrew of 

installed HFC units. You must use the 

service information described 

previously to perform the actions 

required by this AD. 

FAA’s Determination of the Effective 

Date 

Since an unsafe condition exists that 

requires the immediate adoption of this 

AD, we have found that notice and 

opportunity for public comment before 

issuing this AD are impracticable, and 

that good cause exists for making this 

amendment effective in less than 30 

days. 


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