34216 Federal Register / Vol. 74, No. 134 / Wednesday, July 15, 2009 / Rules and Regulations 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0638; Directorate 

Identifier 2009–CE–038–AD; Amendment 

39–15968; AD 2009–15–05] 

RIN 2120–AA64 

Airworthiness Directives; Cessna 

Aircraft Company Models 208 and 

208B Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Cessna Aircraft Company (Cessna) 

Models 208 and 208B airplanes. This 

AD requires you to measure the roll and 

the yaw bridle cable tension (adjusting 

as necessary) and to torque the clamp 

screws. This AD results from two 

reported incidences of slack bridle 

cables with the swaged balls unseating 

from their drum recesses. We are issuing 

this AD to detect and correct loose 

bridle cable clamps, which could result 

in the swaged ball unseating from the 

recess in the servo drum and contacting 

the cable guard pin. This failure could 

lead to very limited control of the 

rudder and/or aileron with consequent 

loss of control. 

DATES: This AD becomes effective on 

July 27, 2009. 

On July 27, 2009, the Director of the 

Federal Register approved the 

incorporation by reference of certain 

publications listed in this AD. 

We must receive any comments on 

this AD by September 14, 2009. 

ADDRESSES: Use one of the following 

addresses to comment on this AD. 

• 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 

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

Washington, DC 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

To get the service information 

identified in this AD, contact Cessna 

Aircraft Company, Product Support, 

P.O. Box 7706; Wichita, Kansas 67277; 

telephone: (316) 517–5800; fax: (316) 

942–9006; Internet: http:// 

www.cessna.com. 

To view the comments to this AD, go 

to http://www.regulations.gov. The 

docket number is FAA–2009–0638; 

Directorate Identifier 2009–CE–038–AD. 

FOR FURTHER INFORMATION CONTACT: Ann 

Johnson, Aerospace Engineer, Wichita 

Aircraft Certification Office (ACO), 1801 

Airport Road, Room 100, Wichita, 

Kansas 67209; telephone: (316) 946– 

4105; fax: (316) 946–4107; E-mail: 

ann.johnson@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We received reports on two Cessna 

Models 208 and 208B production 

airplanes with autopilot heading 

squawks. Upon investigation by the 

manufacturer, technicians found in both 

cases the bridle cable for the autopilot 

aileron servo was slack, and the swaged 

ball was unseated from the drum recess. 

The cause of the bridle cables going 

slack was insufficient torque on the 

bridle cable clamp screws, allowing 

slippage of the bridle cable clamps on 

the roll bridle cable. Since the rudder 

and aileron autopilot interface are 

similar, the same condition could exist 

with the yaw bridle cable. 

This condition, if not corrected, could 

result in the swaged ball unseating from 

the recess in the servo drum and 

contacting the cable guard pin. This 

failure could lead to very limited 

control of the rudder and/or aileron 

with consequent loss of control. 

Relevant Service Information 

We reviewed Cessna Aircraft 

Company Caravan Service Bulletin 

CAB08–9, dated November 24, 2008. 

The service information describes 

procedures for inspecting the bridle 

cables for looseness, adjusting the bridle 

cable tension, and tightening the bridle 

cable clamp screws to the correct 

torque. The manufacturer intends that 

the actions specified in the service 

information adequately address the 

unsafe condition. 

FAA’s Determination and Requirements 

of This AD 

We are issuing this AD because we 

evaluated all the information and 

determined the unsafe condition 

described previously is likely to exist or 

develop on other products of the same 

type design. This AD requires you to 

measure the autopilot roll and yaw 

bridle cable tensions (adjusting as 

necessary) and to torque the bridle cable 

clamp screws. 

FAA’s Determination of the Effective 

Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD. The FAA has found that the risk to 

the flying public justifies waiving notice 

and comment prior to adoption of this 

rule because the swaged ball on the 

bridle cable could unseat from the servo 

drum and contact the cable guard pin. 

This failure could lead to very limited 

control of the rudder and/or aileron. 

Therefore, we determined that notice 

and opportunity for public comment 

before issuing this AD are impracticable 

and that good cause exists for making 

this amendment effective in fewer than 

30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not precede it by notice and an 

opportunity for public comment. We 

invite you to send any written relevant 

data, views, or arguments regarding this 

AD. Send your comments to an address 

listed under the ADDRESSES section. 

Include the docket number ‘‘FAA– 

2009–0638; Directorate Identifier 2009– 

CE–038–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of the AD. We will consider all 

comments received by the closing date 

and may amend the AD in light of 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 

concerning this AD. 

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 


srobinson on DSKHWCL6B1PROD with RULES
Federal Register / Vol. 74, No. 134 / Wednesday, July 15, 2009 / Rules and Regulations 34217 

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 that this AD: 

(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) 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 that 

contains the AD, the regulatory 

evaluation, any comments received, and 

other information on the Internet at 

http://www.regulations.gov; or in person 

at the Docket Management Facility 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

The Docket Office (telephone (800) 647– 

5527) is located at the street address 

stated 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 airworthiness 

directive (AD): 

2009–15–05 Cessna Aircraft Company: 

Amendment 39–15968; Docket No. 

FAA–2009–0638; Directorate Identifier 

2009–CE–038–AD. 

Effective Date 

(a) This AD becomes effective on July 27, 

2009. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to the following 

airplane models and serial numbers that are 

certificated in any category: 

Model Serial No. 

208 ...... 20800500 through 20800504. 

208B .... 208B1216, 208B2001, 208B2003 

through 208B2023, 208B2025 

through 208B2029, 208B2031 

through 208B2037, 208B2040, 

208B2042, and 208B2043. 

Unsafe Condition 

(d) This AD is the result of two reported 

incidences of slack bridle cables with the 

swaged balls unseated from their drum 

recesses. We are issuing this AD to detect and 

correct loose bridle cable clamps, which 

could result in the swaged ball unseating 

from the recess in the servo drum and 

contacting the cable guard pin. This failure 

could lead to very limited control of the 

rudder and/or aileron with consequent loss 

of control. 

Compliance 

(e) To address this problem, you must do 

the following, unless already done: 

Actions Compliance Procedures 

(1) Measure and adjust as necessary, the roll 

bridle cable tension and yaw bridle cable tension, and torque the 12 bridle cable clamp 

screws.

Within the next 10 hours time-in-service after 

July 27, 2009 (the effective date of this AD).

Follow Accomplishment Instructions, paragraphs 2. through 7., of Cessna Aircraft 

Company Caravan Service Bulletin CAB08– 

9, dated November 24, 2008. 

(2) Use the form (Figure 1 of this AD) to report 

the results of the inspections required in 

paragraph (e)(1) of this AD. The Office of 

Management and Budget (OMB) approved 

the information collection requirements contained in this regulation under the provisions 

of the Paperwork Reduction Act of 1980 (44 

U.S.C. 3501 et seq.) and assigned OMB 

Control Number 2120–0056.

Within 10 days after the inspection required in 

paragraph (e)(1). If Cessna Aircraft Company Caravan Service Bulletin CAB08–9, 

dated November 24, 2008, was done before July 27, 2009 (the effective date of this 

AD) the report is not required.

Send the report to the FAA at the address 

specified in paragraph (f) of this AD. 

AD 2009–15–05 INSPECTION REPORT

[If the SB was done before the effective date of this AD, this report does not need to be completed and returned to the Wichita ACO] 

Airplane Model 

Airplane Serial Number 

Did you find the yaw bridle 

cable tension to be within 

the range of 15–25 lbs? 

Did you find the roll bridle 

cable tension to be within 

the range of 10–14 lbs? 

Were any other discrepancies noted during the 

inspection? 


srobinson on DSKHWCL6B1PROD with RULES
34218 Federal Register / Vol. 74, No. 134 / Wednesday, July 15, 2009 / Rules and Regulations 

AD 2009–15–05 INSPECTION REPORT—Continued 

[If the SB was done before the effective date of this AD, this report does not need to be completed and returned to the Wichita ACO] 

Name 

Telephone and/or e-mail address 

Date 

Send report to: 

Ann Johnson, Aerospace Engineer 

ACE–116W, Wichita Aircraft Certification Office 

1801 Airport Road, Room 100 

Wichita, KS 67209 

fax: (316) 946–4107 

e-mail: ann.johnson@faa.gov 

Figure 1 

Alternative Methods of Compliance 

(AMOCs) 

(f) The Manager, Wichita Aircraft 

Certification Office (ACO), 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: Ann 

Johnson, Aerospace Engineer, Wichita 

Aircraft Certification Office (ACO), 1801 

Airport Road, Room 100, Wichita, Kansas 

67209; telephone: (316) 946–4105; fax: (316) 

946–4107; E-mail: ann.johnson@faa.gov. 

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. 

Material Incorporated by Reference 

(g) You must use Cessna Aircraft Company 

Caravan Service Bulletin CAB08–9, dated 

November 24, 2008, to do the actions 

required by this AD, unless the AD specifies 

otherwise. 

(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 Cessna Aircraft Company, 

Product Support, P.O. Box 7706; Wichita, 

Kansas 67277; telephone: (316) 517–5800; 

fax: (316) 942–9006; Internet: http:// 

www.cessna.com. 

(3) You may review copies of the service 

information incorporated by reference for 

this AD at the FAA, Central Region, Office of 

the Regional Counsel, 901 Locust, Kansas 

City, Missouri 64106. For information on the 

availability of this material at the Central 

Region, call (816) 329–3768. 

(4) You may also review copies of the 

service information incorporated by reference 

for this AD 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 Kansas City, Missouri, on July 6, 

2009. 

Kim Smith, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. E9–16465 Filed 7–14–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0832; Directorate 

Identifier 2008–NM–067–AD; Amendment 

39–15965; AD 2009–15–02] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A318, A319, A320, and A321 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: 

In-service experience has shown that a 

fracture of the gerotor pump of the A320 RAT 

[ram air turbine] may occur. This may lead 

to the non-operation of the RAT in case of 

an in-flight deployment. 

The Non-Deployment or NonPressurization of the RAT, associated with a 

double engine failure or a total loss of normal 

electrical power generation constitutes an 

unsafe condition. 

* * * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

August 19, 2009. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of August 19, 2009. 

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: Tim 

Dulin, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–2141; 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 that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on August 4, 2008 (73 FR 

45174). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

In-service experience has shown that a 

fracture of the gerotor pump of the A320 RAT 

[ram air turbine] may occur. This may lead 

to the non-operation of the RAT in case of 

an in-flight deployment. 

The Non-Deployment or NonPressurization of the RAT, associated with a 

double engine failure or a total loss of normal 

electrical power generation constitutes an 

unsafe condition. 

This AD mandates the replacement of the 

affected gerotor pump assembly, which will 

provide the required improved reliability of 

the RAT. 

The implementation of this modification 

was originally managed by an AIRBUS 

monitoring campaign. However, the rate of 

installation of the modification by operators 

has not met the predicted target. As such and 


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