This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by

the Superintendent of Documents. Prices of

new books are listed in the first FEDERAL

REGISTER issue of each week.

Rules and Regulations Federal Register

28587 

Vol. 72, No. 98 

Tuesday, May 22, 2007 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–27213 Directorate 

Identifier 2007–CE–012–AD; Amendment 

39–15055; AD 2007–10–14] 

RIN 2120–AA64 

Airworthiness Directives; British 

Aerospace Regional Aircraft Model 

HP.137 Jetstream Mk.1, Jetstream 

Series 200, Jetstream Series 3101, and 

Jetstream Model 3201 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

the products listed above. This AD 

results from mandatory continuing 

airworthiness information (MCAI) 

issued by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

Cracking has been found in the nose 

landing gear steering jack piston rod adjacent 

to the eye-end. This was caused by the 

application of excessive tightening torque 

applied to the eye-end whilst being 

assembled during component overhaul. 

Failure of the steering jack piston during 

operation will result in loss of nose wheel 

steering, which may lead to loss of 

directional control during critical phases of 

take-off and landing. 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective June 

26, 2007. 

On June 26, 2007, the Director of the 

Federal Register approved the 

incorporation by reference of APPH Ltd. 

Service Bulletin 32–76, Revision 1, 

dated August 2003, as referenced in 

BAE Systems British Aerospace 

Jetstream Series 3100 & 3200 Service 

Bulletin 32–JA030644, Original Issue: 

October 6, 2003, listed in this AD. 

As of May 22, 2003 (68 FR 16195, 

April 3, 2003), the Director of the 

Federal Register approved the 

incorporation by reference of APPH Ltd. 

Service Bulletin 32–76, pages 1, 2, and 

4 through 7, dated October 2002; and 

page 3, Erratum 1, dated November 

2002, as referenced in BAE Systems 

British Aerospace Jetstream Mandatory 

Service Bulletin 32–JA020741, Original 

Issue: November 2, 2002, listed in this 

AD. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

dms.dot.gov or in person at the Docket 

Management Facility, U.S. Department 

of Transportation, 400 Seventh Street, 

SW., Nassif Building, Room PL–401, 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: 

Taylor Martin, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 

Locust, Room 301, Kansas City, 

Missouri 64106; telephone: (816) 329– 

4138; fax: (816) 329–4090. 

SUPPLEMENTARY INFORMATION: 

Streamlined Issuance of AD 

The FAA is implementing a new 

process for streamlining the issuance of 

ADs related to MCAI. The streamlined 

process will allow us to adopt MCAI 

safety requirements in a more efficient 

manner and will reduce safety risks to 

the public. This process continues to 

follow all FAA AD issuance processes to 

meet legal, economic, Administrative 

Procedure Act, and Federal Register 

requirements. We also continue to meet 

our technical decision-making 

responsibilities to identify and correct 

unsafe conditions on U.S.-certificated 

products. 

This AD references the MCAI and 

related service information that we 

considered in forming the engineering 

basis to correct the unsafe condition. 

The AD contains text copied from the 

MCAI and for this reason might not 

follow our plain language principles. 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on March 15, 2007 (72 FR 

12133) and proposed to supersede AD 

2003–07–06, Amendment 39–13102 (68 

FR 16195, April 3, 2003). The NPRM 

proposed to correct an unsafe condition 

for the specified products. The MCAI 

states: 

Cracking has been found in the nose 

landing gear steering jack piston rod adjacent 

to the eye-end. This was caused by the 

application of excessive tightening torque 

applied to the eye-end whilst being 

assembled during component overhaul. 

Failure of the steering jack piston during 

operation will result in loss of nose wheel 

steering, which may lead to loss of 

directional control during critical phases of 

take-off and landing. 

The inspections and any required 

rectification actions detailed in BAe Systems 

Service Bulletin 32–JA030644 and associated 

APPH Service Bulletin 32–76 Revision 1 are 

required to be performed to ensure continued 

airworthiness of the aircraft. 

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 available data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Differences Between This AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have required different 

actions in this AD from those in the 

MCAI in order to follow FAA policies. 

Any such differences are highlighted in 

a NOTE within the AD. 

Costs of Compliance 

We estimate that this AD will affect 

190 products of U.S. registry. We also 

estimate that it will take about 2 workhours per product to comply with basic 

requirements of this AD. The average 

labor rate is $80 per work-hour. Based 


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28588 Federal Register / Vol. 72, No. 98 / Tuesday, May 22, 2007 / Rules and Regulations 

on these figures, we estimate the cost of 

this AD to the U.S. operators to be 

$30,400, or $160 per product. 

In addition, we estimate that any 

necessary follow-on actions will take 

about 8 work-hours and require parts 

costing $5,300, for a cost of $5,940 per 

product. We have no way of 

determining the number of products 

that may need these actions. 

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 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 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 regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD Docket. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://dms.dot.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 the 

NPRM, the regulatory evaluation, any 

comments received, and other 

information. The street address for the 

Docket Office (telephone (800) 647–

5227) is in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

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 FAA amends § 39.13 by 

removing AD 2003–07–06, Amendment 

39–13102 (68 FR 16195, April 3, 2003) 

and adding the following new AD: 

2007–10–14 British Aerospace Regional 

Aircraft: Amendment 39–15055; Docket 

No. FAA–2007–27213; Directorate 

Identifier 2007–CE–012–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective June 26, 2007. 

Affected ADs 

(b) Supersedes AD 2003–07–06, 

Amendment 39–13102. 

Applicability 

(c) This AD applies to Model HP.137 

Jetstream Mk.1, Jetstream Series 200, 

Jetstream Series 3101, and Jetstream Model 

3201 airplanes, all serial numbers, 

certificated in any category. 

Subject 

(d) Air Transport Association of America 

(ATA) Code 32: Landing Gear. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

Cracking has been found in the nose 

landing gear steering jack piston rod adjacent 

to the eye-end. This was caused by the 

application of excessive tightening torque 

applied to the eye-end whilst being 

assembled during component overhaul. 

Failure of the steering jack piston during 

operation will result in loss of nose wheel 

steering, which may lead to loss of 

directional control during critical phases of 

take-off and landing. 

The inspections and any required 

rectification actions detailed in BAe Systems 

Service Bulletin 32–JA030644 and associated 

APPH Service Bulletin 32–76 Revision 1 are 

required to be performed to ensure continued 

airworthiness of the aircraft. 

Retained Requirements of AD 2003–07–06 

(f) Unless already done, do the following 

actions in accordance with the procedures in 

APPH Ltd. Service Bulletin 32–76 (pages 1, 

2, and 4 through 7, dated October 2002; and 

page 3, Erratum 1, dated November 2002), as 

referenced in BAE Systems British Aerospace 

Jetstream Mandatory Service Bulletin 32–

JA020741, Original Issue: November 2, 2002; 

or APPH Ltd. Service Bulletin 32–76, 

Revision 1, dated August 2003, as referenced 

in BAE Systems British Aerospace Jetstream 

Series 3100 & 3200 Service Bulletin 32–

JA030644, dated October 6, 2003. 

(1) Inspect the steering jack piston rod for 

cracks within the next 90 days or 200 

ground-air-ground (GAG) cycles after May 22, 

2003 (the effective date of AD 2003–07–06), 

whichever occurs first. 

(2) If cracks are found, replace the cracked 

steering jack piston rod. Install the new 

steering jack piston rod using a torque setting 

of 175 lbf (pound force) inch or 20 Nm 

(Newton meters) when tightening the end 

fitting and stop bolt before further flight after 

the inspection required in paragraph (f)(1) of 

this AD. 

(3) If no cracks are found, determine the 

torque setting of the steering jack piston rod 

end fitting and stop bolt before further flight 

after the inspection required in paragraph 

(f)(1) of this AD. 

New Requirements of This AD: Actions and 

Compliance 

(g) Unless already done, do the following 

actions: 

(1) Within 90 days after June 26, 2007 (the 

effective date of this AD), recalculate the safe 

life of the steering jack piston rod and retorque the piston rod eye-end in accordance 

with APPH Ltd. Service Bulletin 32–76, 

Revision 1, dated August 2003, as referenced 

in paragraph 2, Part 2 of BAE Systems British 

Aerospace Jetstream Series 3100 & 3200 

Service Bulletin 32–JA030644, dated October 

6, 2003. 

(2) If the piston rod is found unserviceable 

when inspected in accordance with APPH 

Ltd. Service Bulletin 32–76, Revision 1, 

dated August 2003, as referenced in 

paragraph 2, Part 2 of BAE Systems British 

Aerospace Jetstream Series 3100 & 3200 

Service Bulletin 32–JA030644, dated October 

6, 2003, before further flight remove the 

steering jack and replace with a serviceable 

unit. 

(3) As of June 26, 2007 (the effective date 

of this AD), before a steering jack piston rod 

is installed, it must be inspected and the safe 

life determined in accordance APPH Ltd. 

Service Bulletin 32–76, Revision 1, dated 

August 2003, as referenced in paragraph 2 of 

BAE Systems British Aerospace Jetstream 

Series 3100 & 3200 Service Bulletin 32–

JA030644, dated October 6, 2003. 

FAA AD Differences 

Note: This AD differs from the MCAI and/ 

or service information as follows: No 

differences. 


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Federal Register / Vol. 72, No. 98 / Tuesday, May 22, 2007 / Rules and Regulations 28589 

Other FAA AD Provisions 

(h) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Staff, 

FAA, has the authority to approve AMOCs 

for this AD, if requested using the procedures 

found in 14 CFR 39.19. Send information to 

ATTN: Taylor Martin, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4138; fax: (816) 329–

4090. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your appropriate principal inspector 

(PI) in the FAA Flight Standards District 

Office (FSDO), or lacking a PI, your local 

FSDO. 

(2) AMOCs approved for AD 2003–07–06 

are not approved for this AD. 

(3) Airworthy Product: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer or other source, 

use these actions if they are FAA-approved. 

Corrective actions are considered FAAapproved if they are approved by the State 

of Design Authority (or their delegated 

agent). You are required to assure the product 

is airworthy before it is returned to service. 

(4) Reporting Requirements: For any 

reporting requirement in this AD, under the 

provisions of the Paperwork Reduction Act 

(44 U.S.C. 3501 et seq.), the Office of 

Management and Budget (OMB) has 

approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(i) Refer to MCAI Civil Aviation Authority 

AD No. G–2004–0029, dated December 20, 

2004; BAE Systems British Aerospace 

Jetstream Series 3100 & 3200 Service Bulletin 

32–JA030644, dated October 6, 2003; BAE 

Systems British Aerospace Jetstream 

Mandatory Service Bulletin 32–JA020741, 

Original Issue: November 2, 2002; APPH Ltd. 

Service Bulletin 32–76, Revision 1, dated 

August 2003; and APPH Ltd. Service Bulletin 

32–76, pages 1, 2, and 4 through 7, dated 

October 2002; and page 3, Erratum 1, dated 

November 2002, for related information. 

Material Incorporated by Reference 

(j) You must use APPH Ltd. Service 

Bulletin 32–76, Revision 1, dated August 

2003; as referenced in BAE Systems British 

Aerospace Jetstream Series 3100 & 3200 

Service Bulletin 32–JA030644, dated October 

6, 2003; and APPH Ltd. Service Bulletin 32–

76, pages 1, 2, and 4 through 7, dated October 

2002; and page 3, Erratum 1, dated November 

2002; as referenced in BAE Systems British 

Aerospace Jetstream Mandatory Service 

Bulletin 32–JA020741, Original Issue: 

November 2, 2002; to do the actions required 

by this AD, unless the AD specifies 

otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

APPH Ltd. Service Bulletin 32–76, Revision 

1, dated August 2003; as referenced in BAE 

Systems British Aerospace Jetstream Series 

3100 & 3200 Service Bulletin 32–JA030644, 

dated October 6, 2003, under 5 U.S.C. 552(a) 

and 1 CFR part 51. 

(2) On May 22, 2003 (68 FR 16195, April 

3, 2003), the Director of the Federal Register 

approved the incorporation by reference of 

APPH Ltd. Service Bulletin 32–76, pages 1, 

2, and 4 through 7, dated October 2002; and 

page 3, Erratum 1, dated November 2002, as 

referenced in BAE Systems British Aerospace 

Jetstream Mandatory Service Bulletin 32–

JA020741, Original Issue: November 2, 2002. 

(3) For service information identified in 

this AD, contact BAE Systems, Prestwick 

International Airport, Ayshire, KA9 2RW, 

Scotland; telephone: (01292) 675207; fax: 

(01292) 675704. 

(4) You may review copies at the FAA, 

Central Region, Office of the Regional 

Counsel, 901 Locust, Room 506, Kansas City, 

Missouri 64106; 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/ibr-locations.html. 

Issued in Kansas City, Missouri, on May 9, 

2007. 

Charles L. Smalley, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 07–2522 Filed 5–21–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–26112; Directorate 

Identifier 2006–NE–35–AD; Amendment 39–

14837; AD 2006–24–08] 

RIN 2120–AA64 

Airworthiness Directives; Pratt & 

Whitney Canada (P&WC) PW535A 

Turbofan Engines; Correction 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; correction. 

SUMMARY: The FAA is correcting 

airworthiness directive (AD) 2006–24–

08. That AD applies to Pratt & Whitney 

Canada (P&WC) PW535A turbofan 

engines. We published that AD in the 

Federal Register on December 4, 2006 

(71 FR 70284). The fuel manifold part 

number (P/N) 3025267–01 listed in 

paragraph (c) is incorrect. This 

document corrects that P/N. In all other 

respects, the original document remains 

the same. 

EFFECTIVE DATE: Effective May 22, 2007. 

FOR FURTHER INFORMATION CONTACT: Ian 

Dargin, Aerospace Engineer, Engine 

Certification Office, FAA, Engine & 

Propeller Directorate, 12 New 

EnglandExecutive Park, Burlington, MA, 

01803; telephone (781) 238–7178; fax 

(781) 238–7199. 

SUPPLEMENTARY INFORMATION: On 

December 4, 2006 (71 FR 70284), we 

published a final rule AD, FR Doc, E6–

20204, in the Federal Register. That AD 

applies to P&WC PW535A turbofan 

engines. We need to make the following 

correction: 

§ 39.13 [Corrected] 

On page 70286, in the second column, 

in paragraph (c), in the fourth line, 

‘‘3025267–01’’ is corrected to read 

‘‘3052627–01’’. 

Issued in Burlington, Massachusetts, on 

May 14, 2007. 

Peter A. White, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. E7–9719 Filed 5–21–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–22430; Directorate 

Identifier 2005–NE–34–AD; Amendment 39–

15063; AD 2007–11–06] 

RIN 2120–AA64 

Airworthiness Directives; Turbomeca 

Arrius 2F Turboshaft Engines 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD) for 

Turbomeca Arrius 2F turboshaft 

engines. That AD currently requires 

removing from service certain serial 

number (SN) fuel control units (FCUs) 

or replacing the constant delta pressure 

(delta P) diaphragm in those FCUs. This 

AD requires replacing all FCUs not 

incorporating modification Tf 55 with 

FCUs that incorporate modification Tf 

55. This AD results from the European 

Aviation Safety Agency (EASA) and 

Turbomeca expanding the applicability 

to the full population of FCUs installed 

on Arrius 2F turboshaft engines. FCUs 

not incorporating modification Tf 55 are 

susceptible to having an improperly 

assembled constant delta P diaphragm. 

We are issuing this AD to prevent an 

uncommanded engine in-flight 

shutdown on a single-engine helicopter, 

resulting in a forced autorotation 

landing or an accident. 

DATES: This AD becomes effective June 

26, 2007. 

ADDRESSES: You can get the service 

information identified in this AD from 


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