40484 Federal Register / Vol. 74, No. 154 / Wednesday, August 12, 2009 / Rules and Regulations 

747–8/–8F airplanes. The following 

special conditions are in lieu of 

§ 25.361(b): 

1. For turbine engine installations, the 

engine mounts, pylons and supporting 

airframe primary structure (such as the 

affected wing and fuselage primary 

structure) must be designed to 

withstand 1g level flight loads acting 

simultaneously with the maximum 

torque load, considered as limit load, 

imposed by each of the following: 

(a) Sudden engine deceleration due to 

a malfunction which could result in a 

temporary loss of power or thrust; and 

(b) The maximum acceleration of the 

engine. 

2. For auxiliary power unit 

installations, the power unit mounts 

and supporting airframe primary 

structure (such as the affected fuselage 

primary structure) must be designed to 

withstand 1g level flight loads acting 

simultaneously with the maximum 

torque load, considered as limit load, 

imposed by each of the following: 

(a) Sudden auxiliary power unit 

deceleration due to malfunction or 

structural failure; and 

(b) The maximum acceleration of the 

power unit. 

3. For turbine engine installations, the 

engine mounts, pylons and supporting 

airframe primary structure (such as the 

affected wing and fuselage primary 

structure) must be designed to 

withstand 1g flight loads acting 

simultaneously with the transient 

dynamic loads, considered as ultimate 

load, imposed by each of the following: 

(a) Sudden engine stoppage due to the 

loss of any fan, compressor, or turbine 

blade; and separately 

(b) Where applicable to a specific 

engine design, any other engine 

structural failure that results in higher 

loads. 

4. The ultimate loads developed from 

the conditions specified in paragraphs 

3(a) and 3(b) are to be multiplied by a 

factor of 1.0 when applied to engine 

mounts and pylons and multiplied by a 

factor of 1.25 when applied to the 

supporting airframe primary structure 

(such as the affected wing and fuselage 

primary structure). In addition, the 

airplane must be capable of continued 

safe flight considering the aerodynamic 

effects on controllability due to any 

permanent deformation that results from 

the conditions specified in paragraph 3, 

above. 

Issued in Renton, Washington, on July 29, 

2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–19249 Filed 8–11–09; 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; Amendment 

39–15992; AD 2008–16–09 R1] 

RIN 2120–AA64 

Airworthiness Directives; Short 

Brothers Model SD3–60 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are revising an existing 

airworthiness directive (AD) for the 

products listed above. This 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. 

* * * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

September 16, 2009. 

The Director of the Federal Register 

previously approved the incorporation 

by reference of certain publications 

listed in this AD as of September 15, 

2008 (73 FR 46543, August 11, 2008). 

The Director of the Federal Register 

previously approved the incorporation 

by reference of a certain publication 

listed in this AD as of March 14, 2005 

(70 FR 9212, February 25, 2005). 

The Director of the Federal Register 

previously approved the incorporation 

by reference of a certain other 

publication listed in this AD as of 

September August 3, 2004 (69 FR 38813, 

June 29, 2004). 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC. 

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: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD to revise AD 

2008–16–09, amendment 39–15627 (73 

FR 46543, August 11, 2008). The 

existing AD applies to the products 

identified in this AD. The NPRM was 

published in the Federal Register on 

May 20, 2009 (74 FR 23668). That 

NPRM proposed to correct an unsafe 

condition for the specified products. 

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 

extend 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 

European Aviation Safety Agency 

Airworthiness Directive 2007–0107–E, 

dated April 18, 2007 (referred to after 

this as ‘‘the MCAI’’), in the AD docket. 

In addition, we removed paragraphs 

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

AD. Those paragraphs defined the use of 

the term ‘‘service bulletin,’’ as used in 

the AD. 

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 


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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 our FAA 

policies. Any such differences are 

highlighted in a NOTE within the AD. 

Costs of Compliance 

We estimate that this AD will affect 

21 products of U.S. registry. We also 

estimate that it will take about 8 to 12 

work-hours per product to comply with 

the basic requirements of this AD. The 

average labor rate is $80 per work-hour. 

Required parts will 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 parts. 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 

this AD to U.S. operators to be between 

$26,712 and $38,304, or between $1,272 

and $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 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 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 AD and placed it in the AD docket. 

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 the NPRM, 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. 

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 amendment 39–15627 (73 FR 

46543, August 11, 2008) and adding the 

following new AD: 

2008–16–09 R1 Short Brothers PLC: 

Amendment 39–15992. Docket No. 

FAA–2009–0464; Directorate Identifier 

2008–NM–189–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective September 16, 2009. 

Affected ADs 

(b) This AD revises AD 2008–16–09. 

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., 

European Aviation Safety Agency 

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, With Revised 

Service Information 

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 

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) 


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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, With Revised 

Service Information 

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 (n) 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) of This AD 

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 

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. 


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(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. 

Material Incorporated by Reference 

(v) You must use the service information 

contained in Table 2 of this AD to do the 

actions required by this AD, unless the AD 

specifies otherwise. If you do the optional 

terminating action specified in this AD, you 

must use the service information specified in 

Table 3 of this AD to do that action, unless 

the AD specifies otherwise. 

TABLE 2—MATERIAL INCORPORATED BY REFERENCE FOR REQUIRED ACTIONS

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. 

TABLE 3—MATERIAL INCORPORATED BY REFERENCE FOR OPTIONAL ACTIONS

Document Revision Date 

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

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

(1) On September 15, 2008 (73 FR 46543, 

August 11, 2008), the Director of the Federal 

Register previously approved the 

incorporation by reference of Shorts Alert 

Service Bulletin SD360–55–A21, Revision 1, 

dated March 29, 2007; Shorts Service 

Bulletin SD360–55–20, Revision 1, dated 

June 20, 2005; and Shorts Service Bulletin 

SD360–55–20, Revision 2, dated March 29, 

2007. 

(2) On March 14, 2005 (70 FR 9212, 

February 25, 2005), the Director of the 

Federal Register previously approved the 

incorporation by reference of Short Brothers 

Alert Service Bulletin SD360–55–A21, dated 

December 16, 2004. 

(3) On August 3, 2004 (69 FR 38813, June 

29, 2004), the Director of the Federal Register 

previously approved the incorporation by 

reference of Short Brothers Service Bulletin 

SD360–55–20, dated June 26, 2003. 


jlentini on DSKJ8SOYB1PROD with RULES
40488 Federal Register / Vol. 74, No. 154 / Wednesday, August 12, 2009 / Rules and Regulations 

(4) For service information identified in 

this 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. 

(5) You may review copies of the 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. 

(6) You may also review copies of the 

service information that is incorporated by 

reference 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. 

Issued in Renton, Washington, on August 

3, 2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–19181 Filed 8–11–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 95 

[Docket No. 30680; Amdt. No. 482] 

IFR Altitudes; Miscellaneous 

Amendments 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This amendment adopts 

miscellaneous amendments to the 

required IFR (instrument flight rules) 

altitudes and changeover points for 

certain Federal airways, jet routes, or 

direct routes for which a minimum or 

maximum en route authorized IFR 

altitude is prescribed. This regulatory 

action is needed because of changes 

occurring in the National Airspace 

System. These changes are designed to 

provide for the safe and efficient use of 

the navigable airspace under instrument 

conditions in the affected areas. 

DATES: Effective Date: 0901 UTC, August 

27, 2009. 

FOR FURTHER INFORMATION CONTACT: 

Harry Hodges, Flight Procedure 

Standards Branch (AMCAFS–420), 

Flight Technologies and Programs 

Division, Flight Standards Service, 

Federal Aviation Administration, Mike 

Monroney Aeronautical Center, 6500 

South MacArthur Blvd., Oklahoma City, 

OK 73169 (Mail Address: P.O. Box 

25082, Oklahoma City, OK 73125) 

telephone: (405) 954–4164. 

SUPPLEMENTARY INFORMATION: This 

amendment to part 95 of the Federal 

Aviation Regulations (14 CFR part 95) 

amends, suspends, or revokes IFR 

altitudes governing the operation of all 

aircraft in flight over a specified route 

or any portion of that route, as well as 

the changeover points (COPs) for 

Federal airways, jet routes, or direct 

routes as prescribed in part 95. 

The Rule 

The specified IFR altitudes, when 

used in conjunction with the prescribed 

changeover points for those routes, 

ensure navigation aid coverage that is 

adequate for safe flight operations and 

free of frequency interference. The 

reasons and circumstances that create 

the need for this amendment involve 

matters of flight safety and operational 

efficiency in the National Airspace 

System, are related to published 

aeronautical charts that are essential to 

the user, and provide for the safe and 

efficient use of the navigable airspace. 

In addition, those various reasons or 

circumstances require making this 

amendment effective before the next 

scheduled charting and publication date 

of the flight information to assure its 

timely availability to the user. The 

effective date of this amendment reflects 

those considerations. In view of the 

close and immediate relationship 

between these regulatory changes and 

safety in air commerce, I find that notice 

and public procedure before adopting 

this amendment are impracticable and 

contrary to the public interest and that 

good cause exists for making the 

amendment effective in less than 30 

days. 

Conclusion 

The FAA has determined that this 

regulation only involves an established 

body of technical regulations for which 

frequent and routine amendments are 

necessary to keep them operationally 

current. It, therefore—(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) 

does not warrant preparation of a 

regulatory evaluation as the anticipated 

impact is so minimal. For the same 

reason, the FAA certifies that this 

amendment will not have a significant 

economic impact on a substantial 

number of small entities under the 

criteria of the Regulatory Flexibility Act. 

Issued in Washington, DC, on July 24, 

2009. 

John M. Allen, 

Director, Flight Standards Service. 

List of Subjects in 14 CFR Part 95 

Airspace, Navigation (air). 

Adoption of the Amendment 

■ Accordingly, pursuant to the authority 

delegated to me by the Administrator, 

part 95 of the Federal Aviation 

Regulations (14 CFR part 95) is 

amended as follows effective at 0901 

UTC, August 27, 2009. 

■ 1. The authority citation for part 95 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40103, 40106, 

40113, 40114, 40120, 44502, 44514, 44719, 

44721. 

■ 2. Part 95 is amended to read as 

follows: 

REVISIONS TO IFR ALTITUDES & CHANGEOVER POINTS

[Amendment 482 Effective Date August 27, 2009] 

From To MEA MAA 

§ 95.4000 High Altitude RNAV Routes 

§ 95.4016 RNAV Route Q16 Is Amended To Read In Part 

KODIAK, AK VOR/DME #GNSS MEA ............................. MIDDLETON ISLAND, AK VOR/DME ............................. 18000 45000 

Is Amended By Adding 

MIDDLETON ISLAND, AK VOR/DME #GNSS MEA ....... YAKUTAT, AK VOR/DME ................................................ 18000 45000 


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