Federal Register / Vol. 72, No. 50 / Thursday, March 15, 2007 / Proposed Rules 12133 

Actions Compliance Procedures 

(1) Visually inspect the engine mount for any 

cracks.

Initially inspect upon accumulating 1,300 

hours TIS or within the next 100 hours TIS 

after the effective date of this AD, whichever occurs later, unless already done. 

Thereafter, inspect repetitively at intervals 

not to exceed 300 hours TIS.

Follow Snow Engineering Co. Service Letter 

#253, dated December 12, 2005, revised 

January 22, 2007. 

(2) If you find any crack damage, do the following: 

(i) Obtain an FAA-approved repair scheme 

or replacement procedure from the manufacturer; and 

(ii) Repair following the FAA-approved repair scheme or replace the engine mount 

with a new engine mount following the 

replacement procedure. 

Before further flight after any inspection required by paragraph (e)(1) of this AD where 

crack damage is found. If you repair the 

cracked engine mount, then continue to reinspect at intervals not to exceed 300 hours 

TIS, unless the repair scheme states differently. If you replace the engine mount, 

then initially inspect upon accumulating 

1,300 hours TIS and repetitively at intervals 

not to exceed 300 hours TIS.

For obtaining a repair scheme or replacement 

procedure: Contact Air Tractor Inc., P.O. 

Box 485, Olney, Texas 76374; telephone: 

(940) 564–5616; facsimile: (940) 564–5612. 

(3) Report any cracks that you find to the FAA 

at the address specified in paragraph (f) of 

this AD. Include in your report: 

(i) Airplane serial number; 

(ii) Airplane hours TIS and engine mount 

hours TIS; 

(iii) Crack location(s) and size(s); 

(iv) Corrective action taken; and 

(v) Point of contact name and telephone 

number. 

Within the next 30 days after you find the 

cracks or within the next 30 days after the 

effective date of this AD, whichever occurs 

later.

The Office of Management and Budget (OMB) 

approved the information collection requirements contained in this regulation under the 

provisions of the Paperwork Reduction Act 

of 1980 (44 U.S.C. 3501 et seq.) and assigned OMB Control Number 2120–0056. 

Alternative Methods of Compliance 

(AMOCs) 

(f) The Manager, Fort Worth Airplane 

Certification Office, FAA, ATTN: Andrew 

McAnaul, Aerospace Engineer, ASW–150 

(c/o MIDO–43), 10100 Reunion Place, Suite 

650, San Antonio, Texas 78216; telephone: 

(210) 308–3365; facsimile: (210) 308–3370, 

has the authority to approve AMOCs for this 

AD, if requested using the procedures found 

in 14 CFR 39.19. 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. 

(g) AMOCs approved for AD 2006–22–08 

are not approved for this AD. 

Related Information 

(h) To get copies of the service information 

referenced in this AD, contact Air Tractor 

Inc., P.O. Box 485, Olney, Texas 76374; 

telephone: (940) 564–5616; facsimile: (940) 

564–5612. To view the AD docket, go to the 

Docket Management Facility; U.S. 

Department of Transportation, 400 Seventh 

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

Washington, DC, or on the Internet at http:// 

ms.dot.gov. The docket number is Docket No. 

FAA–2007–27212; Directorate Identifier 

2007–CE–011–AD. 

Issued in Kansas City, Missouri, on March 

8, 2007. 

David R. Showers, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E7–4737 Filed 3–14–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–27213; Directorate 

Identifier 2007–CE–012–AD] 

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: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above that would 

supersede an existing AD. This 

proposed AD results from mandatory 

continuing airworthiness information 

(MCAI) originated 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. 

The proposed AD would require actions 

that are intended to address the unsafe 

condition described in the MCAI. 

DATES: We must receive comments on 

this proposed AD by April 16, 2007. 

ADDRESSES: You may send comments by 

any of the following methods: 

• DOT Docket Web Site: Go to 

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

instructions for sending your comments 

electronically. 

• Fax: (202) 493–2251. 

• Mail: Docket Management Facility, 

U.S. Department of Transportation, 400 

Seventh Street, SW., Nassif Building, 

Room PL–401, Washington, DC 20590–

0001. 

• 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. 

• Federal eRulemaking Portal: http:// 

www.regulations.gov. Follow the 

instructions for submitting comments. 

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 this 

proposed AD, 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. 


rmajette on PROD1PC67 with PROPOSALS
12134 Federal Register / Vol. 72, No. 50 / Thursday, March 15, 2007 / Proposed Rules 

Comments will be available in the AD 

docket shortly after receipt. 

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. This 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 proposed AD references the 

MCAI and related service information 

that we considered in forming the 

engineering basis to correct the unsafe 

condition. The proposed AD contains 

text copied from the MCAI and for this 

reason might not follow our plain 

language principles. 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2007–27213; Directorate Identifier 

2007–CE–012–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD because 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 we receive 

about this proposed AD. 

Discussion 

On March 25, 2003, we issued AD 

2003–07–06, Amendment 39–13102 (68 

FR 16195, April 3, 2003). That AD 

required actions intended to address an 

unsafe condition on the products listed 

above. 

Since we issued AD 2003–07–06, 

following the completion of their 

testing, the equipment manufacturer has 

determined that the fatigue life needs 

further revision (reduction) and has 

published inspection criteria and a 

revised formula for calculating the 

piston safe life. This calculation and a 

revised end fitting tightening torque are 

contained in Revision 1 to APPH Ltd. 

Service Bulletin 32–76. As a result, 

pistons, which were previously 

calculated to have significant remaining 

life, may now be unserviceable. 

The Civil Aviation Authority, which 

is the aviation authority for the United 

Kingdom, has issued AD No. G–2004–

0029, dated December 20, 2004 (referred 

to after this as ‘‘the MCAI’’), 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 MCAI requires: 

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. 

You may obtain further information 

by examining the MCAI in the AD 

docket. 

Relevant Service Information 

BAE Systems has issued British 

Aerospace Jetstream Series 3100 & 3200 

Service Bulletin 32–JA030644, dated 

October 6, 2003. APPH Ltd. has issued 

Service Bulletin 32–76, Revision 1, 

dated August 2003. The actions 

described in this service information are 

intended to correct the unsafe condition 

identified in the MCAI. 

FAA’s Determination and Requirements 

of the Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with this State of 

Design Authority, they have notified us 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all 

information and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Differences Between This Proposed 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 proposed 

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 

proposed AD. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 190 products of U.S. 

registry. We also estimate that it would 

take about 2 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $80 per work-hour. 

Based on these figures, we estimate 

the cost of the proposed AD on U.S. 

operators to be $30,400, or $160 per 

product. 

In addition, we estimate that any 

necessary follow-on actions would 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 proposed AD 

would not have federalism implications 


rmajette on PROD1PC67 with PROPOSALS
Federal Register / Vol. 72, No. 50 / Thursday, March 15, 2007 / Proposed Rules 12135 

under Executive Order 13132. This 

proposed AD would 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 proposed 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 regulatory evaluation 

of the estimated costs to comply with 

this proposed AD and placed it in the 

AD docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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 Airworthiness Directive (AD) 

2003–07–06, Amendment 39–13102 (68 

FR 16195, April 3, 2003), and adding 

the following new AD: 

British Aerospace Regional Aircraft: Docket 

No. FAA–2007–27213; Directorate 

Identifier 2007–CE–012–AD. 

Comments Due Date 

(a) We must receive comments by April 16, 

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. 

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 

Mandatory Service Bulletin 32–JA030644, 

Original Issue: October 6, 2003. 

(1) Within the next 90 days or 200 groundair-ground (GAG) cycles after May 22, 2003 

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

whichever occurs first, inspect the steering 

jack piston rod for cracks. 

(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. 

(3) If no cracks are found, determine the 

torque setting of the steering jack piston rod 

end fitting and stop bolt. 

New Requirements of This AD: Actions and 

Compliance 

(g) Unless already done, do the following 

actions: 

(1) Within 90 days after the effective date 

of this AD, recalculate the safe life of the 

steering jack piston rod and re-torque 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 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 Service 

Bulletin 32–JA030644, dated October 6, 2003, 

before further flight remove the steering jack 

and replace with a serviceable unit. 

(3) As of 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 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. 

Other FAA AD Provisions 

(h) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Staff, 

FAA, Small Airplane Directorate, ATTN: 

Taylor Martin, Aerospace Engineer, 901 

Locust, Room 301, Kansas City, Missouri 

64106; telephone: (816) 329–4138; fax: (816) 

329–4090, has the authority to approve 

AMOCs for this AD, if requested using the 

procedures found in 14 CFR 39.19. 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 FAA-approved 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. 

Issued in Kansas City, Missouri, on March 

8, 2007. 

David R. Showers, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E7–4739 Filed 3–14–07; 8:45 am] 

BILLING CODE 4910–13–P 


rmajette on PROD1PC67 with PROPOSALS