Federal Register / Vol. 73, No. 119 / Thursday, June 19, 2008 / Rules and Regulations 34847 

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: 


jlentini on PROD1PC65 with RULES
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. 


jlentini on PROD1PC65 with RULES
Federal Register / Vol. 73, No. 119 / Thursday, June 19, 2008 / Rules and Regulations 34849 

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 

TABLE 1.—MATERIAL INCORPORATED BY REFERENCE

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. 


jlentini on PROD1PC65 with RULES