## 34847 Federal Register / Vol. 73, No. 119 / Thursday, June 19, 2008 / Rules and Regulations
until the action required by paragraph (j) of this AD is accomplished.

(i) Prior to the accumulation of 14,000 total flight hours or 2,250 total flight cycles, whichever occurs first.

(ii) Within 6 months after the effective date of this AD. Action if No Cracking Is Found

(h) If no cracking is found during any inspection required by paragraph (g) of this AD: Before further flight, apply sealant and a torque stripe and install a lockwire on the rudder PCM in accordance with the Accomplishment Instructions, and Figure 1 or Figure 2, as applicable, of Boeing Service Bulletin 747

– 27A2397, Revision 2, dated September 1, 2005. Action if Cracking Is Found

(i) If any cracking is found during any inspection required by paragraph (g) of this AD: Before further flight, do the action in paragraph (i)(1) or (i)(2) of this AD.

(1) Replace the affected PCM with a new or serviceable PCM in accordance with the Accomplishment Instructions of Boeing Service Bulletin 747

– 27A2397, Revision 2, dated September 1, 2005.

(2) Replace the PCM with a PCM that has the new secondary retention device installed as specified in paragraph (j) of this AD. Terminating Action

(j) Within 24 months or 8,400 flight hours after the effective date of this AD, whichever occurs earlier: Install a new secondary retention device for the yaw damper piston assembly in both the upper and lower PCMs by either replacing the existing PCM with a new improved PCM that already has the new secondary retention device, or by modifying, testing, and re-identifying the existing PCM while the PCM is installed on the airplane. Do the installation in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747

– 27A2479, dated November 8, 2007. Doing the installation terminates the inspection requirements of this AD.

Note 1: Boeing Alert Service Bulletin 747

– 27A2479 refers to Parker Service Bulletins 332700

– 27

– 312 and 333200

– 27

– 314, both dated September 13, 2007, as additional sources of service information for modifying the PCM. Prior Accomplishment of Requirements

(k) Actions accomplished before October 13, 2006 (the effective date of AD 2006

– 18

– 17), in accordance with Boeing Alert Service Bulletin 747

– 27A2397, dated July 24, 2003; or Revision 1, dated March 31, 2005; are considered acceptable for compliance with the corresponding requirements of this AD. Parts Installation

(l) As of October 13, 2006, no person may install on any airplane a rudder PCM having a top assembly part number (P/N) 332700

– 1003,

– 1005, or

– 1007; or P/N 333200

– 1003,

– 1005, or

– 1007; unless the PCM has been ultrasonically inspected and found to be without cracks; in accordance with the Accomplishment Instructions of Boeing Service Bulletin 747

– 27A2397, Revision 2, dated September 1, 2005, as specified by paragraph (g) of this AD. Alternative Methods of Compliance (AMOCs)

(m)(1) The Manager, Seattle Aircraft Certification Office, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19.

(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 appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO.

(3) AMOCs approved previously in accordance with AD 2006

– 18

– 17 are approved as AMOCs for the corresponding provisions of paragraphs (g), (h), and (i) of this AD. Material Incorporated by Reference

(n) You must use Boeing Service Bulletin 747

– 27A2397, Revision 2, dated September 1, 2005; and Boeing Alert Service Bulletin 747

– 27A2479, dated November 8, 2007; as applicable; to perform the actions that are required by this AD, unless the AD specifies otherwise.

(1) The Director of the Federal Register approved the incorporation by reference of Boeing Alert Service Bulletin 747

– 27A2479, dated November 8, 2007, in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.

(2) October 13, 2006 (71 FR 52999, September 8, 2006), the Director of the Federal Register approved the incorporation by reference of Boeing Service Bulletin 747

– 27A2397, Revision 2, dated September 1, 2005.

(3) Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124

– 2207, for a copy of this service information. You may review copies at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; 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/ibrlocations.html.

Issued in Renton, Washington, on June 9, 2008. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E8

– 13561 Filed 6

– 18

– 08; 8:45 am]
**BILLING CODE 4910**

**– 13** 

**– P**  

### DEPARTMENT OF TRANSPORTATION **Federal Aviation Administration**
**14 CFR Part 39 [Docket No. FAA** 

**– 2008** 

**– 0275; Directorate**  **Identifier 2007**

**– NM** 

**– 335** 

**– AD; Amendment**  **39**

**– 15565; AD 2008** 

**– 13** 

**– 02]**  **RIN 2120**

**– AA64**  

### Airworthiness Directives; BAE **Systems (Operations) Limited (Jetstream) Model 4101 Airplanes** 
**AGENCY** 

### : Federal Aviation Administration (FAA), Department of Transportation (DOT). **ACTION** 

### : Final rule.
**SUMMARY** 

### : We are adopting a new 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:

Cracks have been found in the propeller blades and propeller hubs, for which ongoing controlling actions issued by the propeller TC [type certificate] holder (McCauley Propeller Systems) have been mandated by FAA Airworthiness Directive (AD) action.

Current FAA ADs related to this subject are 2003

– 17

– 10 (which superseded AD 2003

– 15

– 01), 2004

– 23

– 16, 2005

– 24

– 08 and 2006

– 15

– 13.

Cracking of the blade or hub can ultimately lead to blade release with potentially catastrophic consequences. * * * 

### * * * * *

We are issuing this AD to require actions to correct the unsafe condition on these products. **DATES** 

### : This AD becomes effective July 24, 2008.

The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of July 24, 2008. **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, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98057

– 3356; telephone (425) 227

– 1175; fax (425) 227

– 1149. **SUPPLEMENTARY INFORMATION** 

### :


## 34848 Federal Register / Vol. 73, No. 119 / Thursday, June 19, 2008 / Rules and Regulations

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 13, 2008 (73 FR 13504). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states:

Cracks have been found in the propeller blades and propeller hubs, for which ongoing controlling actions issued by the propeller TC [type certificate] holder (McCauley Propeller Systems) have been mandated by FAA Airworthiness Directive (AD) action.

Current FAA ADs related to this subject are 2003

– 17

– 10 (which superseded AD 2003

– 15

– 01), 2004

– 23

– 16, 2005

– 24

– 08 and 2006

– 15

– 13.

Cracking of the blade or hub can ultimately lead to blade release with potentially catastrophic consequences. BAE Systems has concluded that safety margins can be further improved by introducing operating limitations that will prevent damaging stresses in the propeller assembly, instructing flight crews to place the propeller condition levers in the Flight position during all ground maneuvering.

EASA concurs with this conclusion and this AD therefore requires the replacement of the Propeller Limitations Placard with a new
one.



### Corrective actions include revising the airplane flight manual. You may obtain further information by examining the MCAI in the AD docket. 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 our FAA policies. Any such differences are highlighted in a NOTE within the AD. Costs of Compliance We estimate that this AD will affect about 7 products of U.S. registry. We also estimate that it will take about 2 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 $25 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 the U.S. operators to be $1,295, or $185 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 adding the following new AD:
2008

– 13

– 02 BAE Systems (Operations) Limited (Formerly British Aerospace Regional Aircraft): Amendment 39

– 15565. Docket No. FAA

– 2008

– 0275; Directorate Identifier 2007

–NM

– 335

–AD. Effective Date

(a) This airworthiness directive (AD) becomes effective July 24, 2008. Affected ADs

(b) None. Applicability

(c) This AD applies to BAE Systems (Operations) Limited (Jetstream) Model 4101 airplanes, all serial numbers, certificated in any category. Subject

(d) Air Transport Association (ATA) of America Code 11: Placards and Markings. Reason

(e) The mandatory continuing airworthiness information (MCAI) states:

Cracks have been found in the propeller blades and propeller hubs, for which ongoing controlling actions issued by the propeller TC [type certificate] holder (McCauley Propeller Systems) have been mandated by FAA Airworthiness Directive (AD) action.


## 34849 Federal Register / Vol. 73, No. 119 / Thursday, June 19, 2008 / Rules and Regulations
Current FAA ADs related to this subject are 2003

– 17

– 10 (which superseded AD 2003

– 15

– 01), 2004

– 23

– 16, 2005

– 24

– 08 and 2006

– 15

– 13.

Cracking of the blade or hub can ultimately lead to blade release with potentially catastrophic consequences. BAE Systems has concluded that safety margins can be further improved by introducing operating limitations that will prevent damaging stresses in the propeller assembly, instructing flight crews to place the propeller condition levers in the Flight position during all ground maneuvering.

EASA concurs with this conclusion and this AD therefore requires the replacement of the Propeller Limitations Placard with a new
one.

Corrective actions include revising the airplane flight manual. Actions and Compliance

(f) Within 90 days after the effective date of this AD, unless already done, do the following actions.

(1) Replace the existing Propeller Limitations Placard in the cockpit with a new placard, in accordance with the Accomplishment Instructions of BAE Systems (Operations) Limited Service Bulletin J41

– 11

– 027, dated March 29, 2007.

(2) Revise the BAe Jetstream Series 4100 Flight Manual (FM) to include the information in BAe Jetstream Series 4100 General Amendment G12, approved January 2007, and BAe Jetstream Series 4100 Advance Amendment Bulletin 13, approved April 4, 2007. General Amendment G12 describes a rolling take-off technique and the reduced possibility of landing with ice contaminating the wings, and adds a Gross Height/Pressure Altitude Conversion Chart. Advance Amendment Bulletin 13 introduces procedures for placing the propeller condition levers in the Flight position during all ground maneuvering. Operate the airplane according to the procedures in General Amendment G12 and Advance Amendment Bulletin 13.

Note 1: This may be done by inserting copies of General Amendment G12 and Advance Amendment Bulletin 13 into the FM. When General Amendment G12 and Advance Amendment Bulletin 13 have been included in general revisions of the FM, the general revisions may be inserted in the FM, provided the relevant information in the general revision is identical to that in General Amendment G12 and Advance Amendment Bulletin 13. FAA AD Differences

Note 2: This AD differs from the MCAI and/or service information as follows: No differences. Other FAA AD Provisions

(g) 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 appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO.

(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

(h) Refer to MCAI European Aviation Safety Agency (EASA) Airworthiness Directive 2007

– 0268, dated October 8, 2007; BAE Systems (Operations) Limited Service Bulletin J41

– 11

– 027, dated March 29, 2007; BAe Jetstream Series 4100 General Amendment G12, approved January 2007, to the Jetstream Series 4100 Flight Manual; and BAe Jetstream Series 4100 Advance Amendment Bulletin 13, approved April 4, 2007, to the Jetstream Series 4100 Flight Manual; for related information. Material Incorporated by Reference

(i) You must use the service information specified in Table 1 of this AD to do the actions required by this AD, as applicable, unless the AD specifies otherwise. (The approval date of BAe Jetstream Series 4100 General Amendment G12 is specified only on page 0

– 2

– 4.) BAe Jetstream Series 4100 General Amendment G12 contains the following effective pages: Page

List of Effective Pages Pages 0

– 4

– 1 through 0

– 4

– 6 Date

January 2007 

### T ABLE 

### 1.

— M ATERIAL 

### I NCORPORATED BY 

### R EFERENCE
Service information Date BAe Jetstream Series 4100 Advance Amendment Bulletin 13 to the Jetstream Series 4100 Flight Manual ............................. . April 4, 2007. BAe Jetstream Series 4100 General Amendment G12 to the Jetstream Series 4100 Flight Manual ..................................... .... January, 2007. BAE Systems (Operations) Limited Service Bulletin J41

– 11

– 027 ................................................................................................ March 29, 2007.

(1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51.

(2) For service information identified in this AD, contact British Aerospace Regional Aircraft American Support, 13850 Mclearen Road, Herndon, Virginia 20171.

(3) You may review copies at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; 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/ibrlocations.html. Issued in Renton, Washington, on June 10, 2008. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E8

– 13563 Filed 6

– 18

– 08; 8:45 am]
**BILLING CODE 4910**

**– 13** 

**– P**  

### DEPARTMENT OF TRANSPORTATION **Federal Aviation Administration**
**14 CFR Part 39 [Docket No. FAA** 

**– 2008** 

**– 0296; Directorate**  **Identifier 2007**

**– NM** 

**– 307** 

**– AD; Amendment**  **39**

**– 15567; AD 2008** 

**– 13** 

**– 04]**  **RIN 2120**

**– AA64**  

### Airworthiness Directives; Dassault **Model Mystere-Falcon 20**

**– C5, 20** 

**– D5,**  **and 20**

**– E5 Airplanes** 
**AGENCY** 

### : Federal Aviation Administration (FAA), Department of Transportation (DOT). **ACTION** 

### : Final rule.