23668 Federal Register / Vol. 74, No. 96 / Wednesday, May 20, 2009 / Proposed Rules 

Repair Plan In Lieu of Required Inspections 

(w) A repair plan approved by a Boeing 

Company Authorized Representative or 

Designated Engineering Representative before 

the effective date of this AD is acceptable for 

compliance with the requirements of 

paragraphs (g)(2), (i), (q), (r), (s)(1), and (s)(4) 

of this AD, provided the approval was 

documented via FAA Form 8110–3 or 8100– 

9, and identified scribe line damage in the 

title of the form. 

Alternative Methods of Compliance 

(AMOCs) 

(x)(1) The Manager, Seattle ACO, FAA, has 

the authority to approve AMOCs for this AD, 

if requested in accordance with the 

procedures found in 14 CFR 39.19. Send 

information to ATTN: Wayne Lockett, 

Aerospace Engineer, Airframe Branch, ANM– 

120S, FAA, Seattle Aircraft Certification 

Office (ACO), 1601 Lind Avenue, SW., 

Renton, Washington 98057–3356; telephone 

(425) 917–6447; fax (425) 917–6590. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your principal maintenance inspector 

(PMI) or principal avionics inspector (PAI), 

as appropriate, or lacking a principal 

inspector, your local Flight Standards District 

Office. The AMOC approval letter must 

specifically reference this AD. 

(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 (AR) 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 approval must 

meet the certification basis of the airplane, 

and the approval must specifically refer to 

this AD. 

Issued in Renton, WA, on May 6, 2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–11707 Filed 5–19–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0464; Directorate 

Identifier 2008–NM–189–AD] 

RIN 2120–AA64 

Airworthiness Directives; Short 

Brothers Model SD3–60 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above that would revise 

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: 

There have been several occurrences of 

cracked elevator trim tab balance weight 

attachment brackets. On one occasion, the 

elevator trim tab mass balance weight bracket 

separated from the aircraft. The loss of an 

elevator trim tab mass balance weight bracket 

has the potential to cause damage to an 

aircraft, or cause serious injury to personnel. 

* * * 

* * * * * 

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 June 19, 2009. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–40, 1200 New Jersey Avenue, SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Short 

Brothers PLC, Airworthiness, P.O. Box 

241, Airport Road, Belfast BT3 9DZ, 

Northern Ireland; telephone 

+44(0)2890–462469; fax +44(0)2890– 

468444; e-mail michael.mulholland

@aero.bombardier.com; Internet http:// 

www.bombardier.com. 

You may review copies of the 

referenced service information at the 

FAA, Transport Airplane Directorate, 

1601 Lind Avenue, SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, 

call 425–227–1221 or 425–227–1152. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office 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 Operations 

office (telephone (800) 647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Todd Thompson, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1175; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

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–2009–0464; Directorate Identifier 

2008–NM–189–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 based on those comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.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 July 23, 2008, we issued AD 2008– 

16–09, amendment 39–15627 (73 FR 

46543, August 11, 2008). That AD 

required actions intended to address an 

unsafe condition on the products listed 

above. 

Since we issued AD 2008–16–09, 

Short Brothers advised that SD3–07– 

6011xA brackets manufactured in 2005 

or later have a life limit of 28,800 flight 

hours, per Section 5–00–02 of the Short 

Brothers SD360 Aircraft Maintenance 

Manual (AMM), and as noted in 

Appendix 1 of Shorts Alert Service 

Bulletin SD360–55–A21, Revision 1, 

dated March 29, 2007. In light of this, 

we have revised the existing AD to 

propose extending the life limit of any 

balance weight bracket from 1,750 flight 

hours to 28,800 flight hours. You may 

obtain further information by examining 

the MCAI in the AD docket. 

In addition, we removed paragraphs 

(f) and (l)(1) of the existing AD from this 

proposed AD. Those paragraphs define 

the use of the term ‘‘service bulletin,’’ as 

used in the AD. 

Federal Register / Vol. 74, No. 96 / Wednesday, May 20, 2009 / Proposed Rules 23669 

Relevant Service Information 

Shorts has issued Service Bulletin 

SD360–55–20, Revision 2, dated March 

29, 2007. The actions described in this 

service information are intended to 

correct the unsafe condition identified 

in the MCAI. 

FAA’s Determination and Requirements 

of This 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 the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

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 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 21 products of U.S. registry. 

We also estimate that it would take 

about 8 to 12 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $80 per work-hour. Required 

parts would cost about $632 to $864 per 

product. Where the service information 

lists required parts costs that are 

covered under warranty, we have 

assumed that there will be no charge for 

these costs. As we do not control 

warranty coverage for affected parties, 

some parties may incur costs higher 

than estimated here. Based on these 

figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$26,712 to $38,304, or $1,272 to $1,824 

per product. 

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 

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, Incorporation by reference, 

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 Amendment 39–15627 (73 FR 

46543, August 11, 2008) and adding the 

following new AD: 

Short Brothers PLC: Docket No. FAA–2009– 

0464; Directorate Identifier 2008–NM– 

189–AD. 

Comments Due Date 

(a) We must receive comments by June 19, 

2009. 

Affected ADs 

(b) The proposed AD revises AD 2008–16– 

09, Amendment 39–15627. 

Applicability 

(c) This AD applies to all Shorts Model 

SD3–60 airplanes, certificated in any 

category. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 55: Stabilizers. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) (i.e., EASA 

Airworthiness Directive 2007–0107–E, dated 

April 18, 2007) states: 

There have been several occurrences of 

cracked elevator trim tab balance weight 

attachment brackets. On one occasion, the 

elevator trim tab mass balance weight bracket 

separated from the aircraft. The loss of an 

elevator trim tab mass balance weight bracket 

has the potential to cause damage to an 

aircraft, or cause serious injury to personnel. 

* * * 

* * * * * 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Restatement of Requirements of AD 2004– 

13–08, Amendment 39–13690 

Initial Inspection 

(g) Within 2 months after August 3, 2004 

(the effective date of AD 2004–13–08, 

amendment 39–13690): Do a dye penetrant 

inspection for cracking in the welded joints 

of the balance weight brackets for the left and 

right elevator trim tabs, in accordance with 

the Accomplishment Instructions of Short 

Brothers Service Bulletin SD360–55–20, 

dated June 26, 2003; Shorts Service Bulletin 

SD360–55–20, Revision 1, dated June 20, 

2005; or Shorts Service Bulletin SD360–55– 

20, Revision 2, dated March 29, 2007. 

Investigative and Corrective Actions if No 

Cracking Is Found 

(h) If no cracking is found during the 

inspection required by paragraph (g) of this 

AD, do the actions required by paragraphs 

(h)(1) and (h)(2) of this AD at the applicable 

compliance times. 

(1) Repeat the inspection required by 

paragraph (g) of this AD at intervals not to 

23670 Federal Register / Vol. 74, No. 96 / Wednesday, May 20, 2009 / Proposed Rules 

exceed 4,800 flight hours until the bracket is 

replaced per paragraph (h)(2) or (i) of this 

AD. 

(2) Prior to the accumulation of 28,800 

total flight hours, or within 6 months after 

August 3, 2004, whichever occurs later: 

Replace any bracket that has not been 

replaced per paragraph (i) of this AD with a 

new bracket or with a serviceable bracket that 

has been inspected in accordance with 

paragraph (g) of this AD. Replace in 

accordance with the Accomplishment 

Instructions of Short Brothers Service 

Bulletin SD360–55–20, dated June 26, 2003; 

Shorts Service Bulletin SD360–55–20, 

Revision 1, dated June 20, 2005; or Shorts 

Service Bulletin SD360–55–20, Revision 2, 

dated March 29, 2007. Replacement of the 

brackets constitutes terminating action for 

the repetitive inspections required by 

paragraph (h)(1) of this AD. 

Corrective Actions if Any Cracking Is Found 

(i) If any cracking is found during any 

inspection required by paragraph (g) or (h) of 

this AD: Before further flight, accomplish the 

applicable action in paragraph (i)(1) or (i)(2) 

of this AD in accordance with the 

Accomplishment Instructions of Short 

Brothers Service Bulletin SD360–55–20, 

dated June 26, 2003; Shorts Service Bulletin 

SD360–55–20, Revision 1, dated June 20, 

2005; or Shorts Service Bulletin SD360–55– 

20, Revision 2, dated March 29, 2007. 

(1) For airplanes that have accumulated 

less than 28,800 flight hours and on which 

all cracking on brackets is less than 0.25 inch 

in length: Repair the affected bracket in 

accordance with Part B of the 

Accomplishment Instructions of Short 

Brothers Service Bulletin SD360–55–20, 

dated June 26, 2003; Shorts Service Bulletin 

SD360–55–20, Revision 1, dated June 20, 

2005; or Shorts Service Bulletin SD360–55– 

20, Revision 2, dated March 29, 2007 

(including the additional dye penetrant 

inspection of the repaired welded joint); and 

repeat the inspection required by paragraph 

(g) of this AD at intervals not to exceed 4,800 

flight hours; or replace the bracket in 

accordance with paragraph (h)(2) of this AD. 

Replacement of the bracket constitutes 

terminating action for the repetitive 

inspections. 

(2) For any airplane on which any cracking 

on a bracket is 0.25 inch in length or greater, 

and for any airplane that has accumulated 

28,800 flight hours or more on which any 

cracking of any length is found on a bracket: 

Replace the affected bracket with a new 

bracket or with a serviceable bracket that has 

been inspected in accordance with paragraph 

(g) of this AD. Replacement of the bracket 

constitutes terminating action for the 

repetitive inspections required by paragraph 

(i)(1) of this AD. 

Refitting 

(j) Before further flight following any 

inspection per paragraph (g) or (h) of this AD; 

or before further flight following repair or 

replacement of a bracket per paragraph (h)(2) 

or (i) of this AD: Refit the balance weights, 

covers, and trim tabs, in accordance with the 

Accomplishment Instructions of Short 

Brothers Service Bulletin SD360–55–20, 

dated June 26, 2003; Shorts Service Bulletin 

SD360–55–20, Revision 1, dated June 20, 

2005; or Shorts Service Bulletin SD360–55– 

20, Revision 2, dated March 29, 2007. Where 

the Accomplishment Instructions of Short 

Brothers Service Bulletin SD360–55–20, 

dated June 26, 2003; Shorts Service Bulletin 

SD360–55–20, Revision 1, dated June 20, 

2005; or Shorts Service Bulletin SD360–55– 

20, Revision 2, dated March 29, 2007; specify 

to contact the manufacturer for disposition of 

certain conditions while refitting, obtain 

further disposition instructions from the 

Manager, International Branch, ANM–116, 

Transport Airplane Directorate, FAA; or the 

European Aviation Safety Agency (EASA) (or 

its delegated agent). 

Parts Installation 

(k) As of August 3, 2004, no person may 

install on any airplane a balance weight 

bracket unless the welded joint has been 

inspected in accordance with paragraph (g) of 

this AD. 

Restatement of Requirements of AD 2005– 

04–13, Amendment 39–13985 

Return of Parts to Manufacturer Not 

Required 

(l) Although the Accomplishment 

Instructions of Short Brothers Alert Service 

Bulletin SD360–55–A21, dated December 16, 

2004; or Shorts Alert Service Bulletin 

SD360–55–A21, Revision 1, dated March 29, 

2007; specify to return subject parts to the 

manufacturer, this AD does not include that 

requirement. 

Repetitive Inspections 

(m) For airplanes equipped with balance 

weight brackets of the elevator trim tabs 

having part number SD3–07–6011xA, and 

having a serial number beginning with ‘‘X3’’ 

or ‘‘X4’’: Prior to the accumulation of 250 

flight hours since installation of the subject 

balance weight bracket of the elevator trim 

tab, or within 30 flight hours after March 14, 

2005 (the effective date of AD 2005–04–13), 

whichever is later, do a dye penetrant 

inspection for cracking of the balance weight 

brackets for the left and right elevator trim 

tabs, in accordance with Short Brothers Alert 

Service Bulletin SD360–55–A21, dated 

December 16, 2004; or Shorts Alert Service 

Bulletin SD360–55–A21, Revision 1, dated 

March 29, 2007. 

(1) For a balance weight bracket on which 

no cracking is found: Do paragraph (o) of this 

AD, and repeat the inspection thereafter at 

intervals not to exceed 250 flight hours until 

paragraph (m) of this AD is accomplished. 

(2) For a balance weight bracket on which 

any cracking is found: Before further flight, 

replace the bracket with a new or reworked 

balance weight bracket that conforms to the 

approved design standard, in accordance 

with Short Brothers Alert Service Bulletin 

SD360–55–A21, dated December 16, 2004; or 

Shorts Alert Service Bulletin SD360–55–A21, 

Revision 1, dated March 29, 2007; and do 

paragraph (o) of this AD. 

Optional Terminating Action 

(n) For airplanes equipped with balance 

weight brackets of the elevator trim tabs 

having part number SD3–07–6011xA, and 

having a serial number beginning with ‘‘X3’’ 

or ‘‘X4’’: Replacement of any subject balance 

weight bracket with a new or reworked 

balance weight bracket that conforms to the 

approved design standard, in accordance 

with the Accomplishment Instructions of 

Short Brothers Alert Service Bulletin SD360– 

55–A21, dated December 16, 2004; or Shorts 

Alert Service Bulletin SD360–55–A21, 

Revision 1, dated March 29, 2007; constitutes 

terminating action for the repetitive 

inspections required by paragraph (m) of this 

AD for the replaced bracket. 

Refitting 

(o) For airplanes equipped with balance 

weight brackets of the elevator trim tabs 

having part number SD3–07–6011xA, and 

having a serial number beginning with ‘‘X3’’ 

or ‘‘X4:’’ Before further flight following any 

inspection or replacement of a bracket in 

accordance with paragraphs (m) and (n) of 

this AD: Refit the balance weights, covers, 

and trim tabs, in accordance with the 

Accomplishment Instructions of Short 

Brothers Alert Service Bulletin SD360–55– 

A21, dated December 16, 2004; or Shorts 

Alert Service Bulletin SD360–55–A21, 

Revision 1, dated March 29, 2007. Where the 

Accomplishment Instructions of Short 

Brothers Alert Service Bulletin SD360–55– 

A21, dated December 16, 2004; or Shorts 

Alert Service Bulletin SD360–55–A21, 

Revision 1, dated March 29, 2007; specify to 

contact the manufacturer for disposition of 

certain conditions while refitting, obtain 

further disposition instructions from the 

Manager, International Branch, ANM–116, 

Transport Airplane Directorate, FAA; or the 

European Aviation Safety Agency (EASA) (or 

its delegated agent). 

Parts Installation 

(p) For all airplanes: As of March 14, 2005, 

no person may install, on any airplane 

subject to this AD, a balance weight bracket 

having part number SD3–07–6011xA, and 

having a serial number beginning with ‘‘X3’’ 

or ‘‘X4,’’ unless the bracket is also marked 

‘‘Rework batch number R–Bxxxxx’’ (where 

‘‘xxxxx’’ is a number). 

Restatement of Requirements of AD 2008– 

16–09, Amendment 39–15627, With 

Extended Repetitive Interval in Paragraph 

(q)(2) 

Inspection(s) and Replacements 

(q) For airplanes equipped with balance 

weight brackets of the elevator trim tabs 

having part number SD3–07–6011xA 

manufactured in the year 2003 or 2004, 

including reworked brackets, installed in 

accordance with paragraph (h)(2), (i)(2), or 

(n) of this AD, as applicable: Do the actions 

specified in paragraphs (q)(1) and (q)(2) of 

this AD in accordance with Parts A and B of 

the Accomplishment Instructions of Shorts 

Alert Service Bulletin SD360–55–A21, 

Revision 1, dated March 29, 2007. 

(1) Within 30 flight hours after September 

15, 2008 (the effective date of AD 2008–16– 

09) or within 250 flight hours since 

installation of the balance weight brackets of 

the elevator trim tabs or since the last 

inspection required by paragraph (g), (h)(1), 

(i)(1), or (m) of this AD, whichever occurs 

Federal Register / Vol. 74, No. 96 / Wednesday, May 20, 2009 / Proposed Rules 23671 

later: Do a dye penetrant inspection to detect 

cracks of the balance weight brackets of the 

elevator trim tabs. 

(i) If no crack is detected, repeat the dye 

penetrant inspection at intervals not to 

exceed 250 flight hours, until the 

replacement required by paragraph (q)(2) of 

this AD is done. 

(ii) If any crack is detected, before further 

flight, do the replacement specified in 

paragraph (q)(2) of this AD. 

(2) Before the accumulation of 1,750 flight 

hours since installation of the balance weight 

brackets of the elevator trim tabs, or within 

180 days after September 15, 2008, 

whichever occurs later: Replace the balance 

weight brackets with new balance weight 

brackets manufactured in 2005 or later. 

Thereafter, replace any balance weight 

bracket with a new bracket manufactured in 

2005 or later at intervals not to exceed the 

accumulation of 28,800 flight hours on that 

bracket. Accomplishment of the initial 

replacement ends the repetitive inspection 

requirements of this AD. 

(r) For airplanes equipped with balance 

weight brackets of the elevator trim tabs 

having part number SD3–31–6213xB 

inspected in accordance with paragraph (g), 

(h)(1), or (i)(1) of this AD and retained or 

refitted following approved repair in 

accordance with paragraph (j) of this AD: Do 

the actions specified in paragraphs (r)(1) and 

(r)(2) of this AD in accordance with Parts A 

and B of the Accomplishment Instructions of 

Shorts Alert Service Bulletin SD360–55–20, 

Revision 2, dated March 29, 2007. 

(1) Within 4,800 flight hours since last 

inspection, or within 180 days after 

September 15, 2008, whichever occurs later, 

and thereafter at intervals not to exceed 4,800 

flight hours: Do a dye penetrant inspection to 

detect cracks of the balance weight brackets 

of the elevator trim tabs. 

(i) If no crack is detected, repeat the dye 

penetrant inspection at intervals not to 

exceed 4,800 flight hours, until the 

replacement required by paragraph (r)(2) of 

this AD is done. 

(ii) If any crack is detected, before further 

flight, do the replacement specified in 

paragraph (r)(2) of this AD. 

(2) Before the accumulation of 28,800 flight 

hours since any balance weight bracket of the 

elevator trim tabs is new, or within 180 days 

after September 15, 2008, whichever occurs 

later: Replace the balance weight brackets 

with new balance weight brackets 

manufactured in 2005 or later. Thereafter, 

replace any balance weight bracket with a 

new bracket manufactured in 2005 or later at 

intervals not to exceed the accumulation of 

28,800 flight hours on that bracket. 

Accomplishment of the initial replacement 

ends the repetitive inspection requirements 

of this AD. 

Part Installation 

(s) For all airplanes: As of September 15, 

2008, no person may install, on any airplane, 

a balance weight bracket of the elevator trim 

tab manufactured earlier than 2005. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: No 

Differences. 

Other FAA AD Provisions 

(t) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, 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: Todd Thompson, 

Aerospace Engineer, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

227–1175; fax (425) 227–1149. Before using 

any approved AMOC on any airplane to 

which the AMOC applies, notify your 

principal maintenance inspector (PMI) or 

principal avionics inspector (PAI), as 

appropriate, or lacking a principal inspector, 

your local Flight Standards District Office. 

(2) 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. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, under the 

provisions of the Paperwork Reduction Act, 

the Office of Management and Budget (OMB) 

has approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(u) Refer to MCAI EASA Airworthiness 

Directive 2007–0107–E, dated April 18, 2007, 

and the service bulletins identified in Table 

1 of this AD for related information. 

TABLE 1—RELATED SERVICE INFORMATION

Document Revision Date 

Short Brothers Alert Service Bulletin SD360–55–A21 .............................................................................. Original December 16, 2004. 

Short Brothers Service Bulletin SD360–55–20 ......................................................................................... Original June 26, 2003. 

Shorts Alert Service Bulletin SD360–55–A21 ........................................................................................... 1 March 29, 2007. 

Shorts Service Bulletin SD360–55–20 ...................................................................................................... 1 June 20, 2005. 

Shorts Service Bulletin SD360–55–20 ...................................................................................................... 2 March 29, 2007. 

Issued in Renton, WA, on May 11, 2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–11709 Filed 5–19–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0463; Directorate 

Identifier 2008–NM–065–AD] 

RIN 2120–AA64 

Airworthiness Directives; BAE 

Systems (Operations) Limited 

(Jetstream) Model 4101 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above. 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: 

A failure mode has been identified that can 

lead to loss of a nose wheel. Any 

combination of excessive wear and/or 

adverse tolerances on the axle inner cone, 

outer cone or wheel hub splined sleeve cones 

can result in the loss of the critical gap 

between the inner flange face of the wheel 

outer cone and the axle end face. If this gap 

is lost, it can result in the wheel having free 

play along the length of the axle. This 

condition, if not corrected, can result in 

breakage of the wheel nut lock plate leading 

to unscrewing of the wheel retention nut and