Federal Register / Vol. 72, No. 82 / Monday, April 30, 2007 / Rules and Regulations 21083 

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/ibr-locations.html. 

TABLE 1.—MATERIAL INCORPORATED

BY REFERENCE

Boeing 

Service 

Bulletin 

Revision 

level Date 

777–27– 

0034.

1 .............. April 20, 2006. 

777–57– 

0054.

Original ... February 23, 2006. 

777–57A– 

0048.

1 .............. June 9, 2005. 

Issued in Renton, Washington, on April 17, 

2007. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E7–7853 Filed 4–27–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–27558; Directorate 

Identifier 2007–NM–053–AD; Amendment 

39–15036; AD 2007–06–52] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 737–800 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: This document publishes in 

the Federal Register an amendment 

adopting airworthiness directive (AD) 

2007–06–52 that was sent previously to 

all known U.S. owners and operators of 

Boeing Model 737–800 series airplanes 

by individual notices. This AD requires 

inspecting spoilers to determine spoiler 

position after every landing and after 

any rejected takeoff maneuvers. For 

airplanes on which any spoiler is found 

in the up position with the speedbrake 

handle in the down position, this AD 

requires replacement of the flight 

spoiler actuator with a flight spoiler 

actuator having a certain part number. 

This AD also requires an operational 

test of the speedbrake control system 

after any maintenance actions that 

operate the spoiler system and 

replacement of the flight spoiler 

actuator if necessary. This AD also 

provides for optional terminating action 

for those requirements. In addition, this 

AD requires you to report to the 

manufacturer any spoiler panel that is 

found in the up position with the 

speedbrake handle in the down 

position. This AD results from a report 

of seven flight spoiler actuator jams on 

Model 737–800 Short Field Performance 

airplanes. We are issuing this AD to 

detect and correct any spoiler panel that 

is found in the up position with the 

speedbrake handle in the down 

position, which could result in a spoiler 

actuator hardover, and could cause the 

spoiler surface to jam in the fully 

extended position. Two or more 

hardover failures of the spoiler surfaces 

in the up direction on the same wing, 

if undetected prior to takeoff, can cause 

significant roll and consequent loss of 

control of the airplane. 

DATES: This AD becomes effective May 

7, 2007 to all persons except those 

persons to whom it was made 

immediately effective by emergency AD 

2007–06–52, issued March 14, 2007, 

which contained the requirements of 

this amendment. 

The incorporation by reference of a 

certain publication listed in the AD is 

approved by the Director of the Federal 

Register as of May 7, 2007. 

We must receive comments on this 

AD by June 29, 2007. 

ADDRESSES: Use one of the following 

addresses to submit comments on this 

AD. 

• DOT Docket Web site: Go to 

http://dms.dot.gov and follow the 

instructions for sending your comments 

electronically. 

• Government-wide rulemaking Web 

site: Go to http://www.regulations.gov 

and follow the instructions for sending 

your comments electronically. 

• Mail: Docket Management Facility; 

U.S. Department of Transportation, 400 

Seventh Street, SW., Nassif Building, 

Room PL–401, Washington, DC 20590. 

• Fax: (202) 493–2251. 

• Hand Delivery: Room PL–401 on 

the plaza level of the Nassif Building, 

400 Seventh Street, SW., Washington, 

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

through Friday, except Federal holidays. 

Contact Boeing Commercial 

Airplanes, P.O. Box 3707, Seattle, 

Washington 98124–2207, for service 

information identified in this AD. 

FOR FURTHER INFORMATION CONTACT: 

Kelly McGuckin, Aerospace Engineer, 

Systems and Equipment Branch, ANM–

130S, FAA, Seattle Aircraft Certification 

Office, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 917–6490; fax (425) 917–6590. 

SUPPLEMENTARY INFORMATION: On March 

14, 2007, we issued emergency AD 

2007–06–52, which applies to certain 

Boeing Model 737–800 series airplanes. 

Background 

On March 13, 2007, the FAA issued 

emergency AD 2007–06–51 for certain 

Boeing Model 737–800 series airplanes. 

That AD requires inspecting spoilers to 

determine spoiler position after every 

landing and after any rejected takeoff 

maneuvers. For airplanes on which any 

spoiler is found in the up position with 

the speedbrake handle in the down 

position, that AD requires replacement 

of the flight spoiler actuator with a flight 

spoiler actuator having a certain part 

number. That AD also requires an 

operational test of the speedbrake 

control system after any maintenance 

actions that operate the spoiler system 

and replacement of the flight spoiler 

actuator if necessary. That AD also 

provides for optional terminating action 

for those requirements. In addition, that 

AD requires you to report to the 

manufacturer any spoiler panel that is 

found in the up position with the 

speedbrake handle in the down 

position. 

That AD resulted from a report of 

seven flight spoiler actuator jams on 

Model 737–800 Short Field Performance 

(SFP) airplanes. Two reports involved 

in-service airplanes that were 

discovered during a routine 

maintenance walk-around and were 

believed to have occurred on the 

previous landing during auto 

speedbrake extension. Five other reports 

occurred during spoiler system testing 

at Boeing prior to delivery. An 

additional two reports of spoiler 

actuator input lever binding were 

identified during bench testing after 

Boeing began to investigate this issue. 

The two in-service failures of flight 

spoilers resulted in the spoilers not 

retracting after the speedbrake handle 

was moved to the DOWN position after 

landing, on a Boeing Model 737–800 

airplane equipped with an SFP package. 

In both of these cases, the spoiler was 

discovered in the full-extended position 

during a routine maintenance walkaround. The spoiler remained in the 

full-extended position after cycling of 

the speedbrake handle. 

Further investigation revealed that the 

spoiler actuator failure is most likely to 

occur when the speedbrakes are 

deployed on the ground (automatically 

or manually) for either a rejected takeoff 

or normal landing. The takeoff 


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21084 Federal Register / Vol. 72, No. 82 / Monday, April 30, 2007 / Rules and Regulations 

configuration warning will not sound if 

any flight spoiler remains extended with 

the speedbrake handle in the DOWN 

position. The cause of the failure has 

been identified as interference within 

the actuator main control valve. 

This condition, if not corrected, could 

result in a spoiler actuator hardover, 

which could cause the spoiler surface to 

jam in the fully extended position. Two 

or more hardover failures of the spoiler 

surfaces in the up direction on the same 

wing, if undetected prior to takeoff, can 

cause significant roll and consequent 

loss of control of the airplane. 

Actions Since Issuance of Previous AD 

Since that AD was issued, we have 

become aware of two incorrect part 

numbers identified throughout 

emergency AD 2007–06–51. The 

identified incorrect part numbers do not 

exist. The incorrect part numbers were 

for the replacement flight spoiler 

actuator and the flight spoiler actuator 

that may no longer be installed. 

In light of this, we have determined 

that emergency AD 2007–06–51 must be 

superseded to reflect the correct part 

numbers. 

Relevant Service Information 

We have reviewed Boeing 737 Flight 

Crew Operations Manual Bulletin No. 

TBC–67, dated March 5, 2007. The 

bulletin describes procedures for 

inspecting spoilers to determine spoiler 

position after landing and after any 

rejected takeoff maneuvers. For 

airplanes on which any spoiler is found 

in the up position with the speedbrake 

handle in the down position, the 

bulletin specifies to contact 

maintenance. 

FAA’s Determination and Requirements 

of This AD 

Since the unsafe condition described 

is likely to exist or develop on other 

airplanes of the same type design, we 

issued emergency AD 2007–06–52 to 

detect and correct any spoiler panel that 

is found in the up position with the 

speedbrake handle in the down 

position, which could result in a spoiler 

actuator hardover, and could cause the 

spoiler surface to jam in the fully 

extended position. Two or more 

hardover failures of the spoiler surfaces 

in the up direction on the same wing, 

if undetected prior to takeoff, can cause 

significant roll and consequent loss of 

control of the airplane. This new AD 

supersedes emergency AD 2007–06–51. 

This new AD requires the actions 

specified in emergency AD 2007–06051, 

but corrects certain part numbers. This 

AD requires accomplishing the actions 

specified in the service information 

described previously, except as 

described in ‘‘Differences Between This 

AD and the Service Information.’’

We found that immediate corrective 

action was required; therefore, notice 

and opportunity for prior public 

comment thereon were impracticable 

and contrary to the public interest, and 

good cause existed to make the AD 

effective immediately by individual 

notices issued on March 14, 2007, to all 

known U.S. owners and operators of 

Boeing Model 737–800 series airplanes. 

These conditions still exist, and the AD 

is hereby published in the Federal 

Register as an amendment to section 

39.13 of the Federal Aviation 

Regulations (14 CFR 39.13) to make it 

effective to all persons. 

Differences Between This AD and the 

Service Information 

In addition to the inspection specified 

in the service information, this AD also 

requires that, after any maintenance 

action that operates the spoiler system, 

the ‘‘Speedbrake Control System 

Operational Test’’ specified in Chapter 

27–62–00 of the Boeing 737–600/700/ 

800/900 Aircraft Maintenance Manual 

(AMM) be accomplished. This AD also 

specifies that the Master Minimum 

Equipment List Item 27–7, ‘‘Auto Speed 

Brake System,’’ is no longer applicable 

to Model 737–800 series airplanes 

equipped with an SFP package. This AD 

also provides an optional terminating 

action of installing flight spoiler 

actuator, part number (P/N) 

P665A0001–01 or higher dash number, 

in all eight flight spoiler positions. 

Although the service information 

specifies that operators may contact 

maintenance for disposition if any 

spoiler remains in the up position with 

the speedbrake handle in the down 

position, this AD requires operators to 

replace the flight spoiler actuator with 

a flight spoiler actuator, having P/N 

P665A0001–01 or higher dash number, 

using a method approved by the FAA. 

Operators should note that the service 

information specifies doing an 

inspection. However, this AD requires 

doing a ‘‘visual check,’’ which may be 

done by qualified ground personnel or 

flightcrew. We have determined that 

these visual checks may be properly 

performed by flightcrew because the 

checks do not require tools, precision 

measuring equipment, training, or pilot 

logbook endorsements, or the use of or 

reference to technical data that are not 

contained in the body of the AD. 

Interim Action 

We consider this AD interim action. 

We are currently considering requiring 

the replacement of the flight spoiler 

actuator, which will constitute 

terminating action for the visual checks 

and operational tests required by this 

AD action. 

Comments Invited 

This AD is a final rule that involves 

requirements that affect flight safety and 

was not preceded by notice and an 

opportunity for public comment; 

however, we invite you to submit any 

relevant written data, views, or 

arguments regarding this AD. Send your 

comments to an address listed in the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2007–27558; Directorate Identifier 

2007–NM–053–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of the AD that might suggest a 

need to modify it. 

We will post all comments we 

receive, without change, to http:// 

dms.dot.gov, including any personal 

information you provide. We will also 

post a report summarizing each 

substantive verbal contact with FAA 

personnel concerning this AD. Using the 

search function of that Web site, anyone 

can find and read the comments in any 

of our dockets, including the name of 

the individual who sent the comment 

(or signed the comment on behalf of an 

association, business, labor union, etc.). 

You may review the DOT’s complete 

Privacy Act Statement in the Federal 

Register published on April 11, 2000 

(65 FR 19477–78), or you may visit 

http://dms.dot.gov. 

Examining the Docket 

You may examine the AD docket on 

the Internet at http://dms.dot.gov, or in 

person at the Docket Management 

Facility office between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. The Docket 

Management Facility office (telephone 

(800) 647–5227) is located on the plaza 

level of the Nassif Building at the DOT 

street address stated in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after the Docket 

Management System receives them. 

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 


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Federal Register / Vol. 72, No. 82 / Monday, April 30, 2007 / Rules and Regulations 21085 

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 have 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. 

The FAA has determined that this 

regulation is an emergency regulation 

that must be issued immediately to 

correct an unsafe condition in aircraft, 

and that it is not a ‘‘significant 

regulatory action’’ under Executive 

Order 12866. It has been determined 

further that this action involves an 

emergency regulation under DOT 

Regulatory Policies and Procedures (44 

FR 11034, February 26, 1979). If this 

emergency regulation is later deemed 

significant under DOT Regulatory 

Policies and Procedures, we will 

prepare a final regulatory evaluation 

and place it in the AD Docket. See the 

ADDRESSES section for a location to 

examine the regulatory evaluation, if 

filed. 

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): 

2007–06–52 Boeing: Amendment 39–15036. 

Docket No. FAA–2007–27558; 

Directorate Identifier 2007–NM–053–AD. 

Effective Date 

(a) This AD becomes effective May 7, 2007, 

to all persons except those persons to whom 

it was made immediately effective by 

emergency AD 2007–06–52, issued on March 

14, 2007, which contained the requirements 

of this amendment. 

Affected ADs 

(b) This AD supersedes emergency AD 

2007–06–51, issued March 13, 2007. 

Applicability 

(c) This AD applies to the Boeing Model 

737–800 series airplanes, certificated in any 

category, serial numbers 32685, 34277 

through 34281 inclusive, 34474, 34475, 

34654 through 34656 inclusive, 34690, 

34948, 34949, 35091 through 35093 

inclusive, 35103, 35134, 35176 through 

35183 inclusive, 35330, 35331, 35558, 35559, 

and 36323 through 36328 inclusive. 

Unsafe Condition 

(d) This AD results from a report of seven 

flight spoiler actuator jams on Model 737–

800 Short Field Performance (SFP) airplanes. 

The cause of the failure has been identified 

as interference within the actuator main 

control valve. We are issuing this AD to 

detect and correct any spoiler panel that is 

found in the up position with the speedbrake 

handle in the down position, which could 

result in a spoiler actuator hardover, and 

could cause the spoiler surface to jam in the 

fully extended position. Two or more 

hardover failures of the spoiler surfaces in 

the up direction on the same wing, if 

undetected prior to takeoff, can cause 

significant roll and consequent loss of control 

of the airplane. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Visual Check and Corrective Action 

(f) Within 24 clock hours after the effective 

date of this AD, do the actions specified in 

paragraphs (f)(1), (f)(2), and (f)(3) of this AD, 

as applicable. The visual checks required by 

paragraphs (f)(1) and (f)(2) of this AD may be 

performed by qualified personnel or 

flightcrew, and must be entered into the 

aircraft records showing compliance with 

this AD in accordance with 14 CFR 43.9(b) 

and 14 CFR 121.363 and 121.380. 

(1) After every landing, visually check the 

spoilers to determine spoiler position, in 

accordance with Boeing 737 Flight Crew 

Operations Manual Bulletin No. TBC–67, 

dated March 5, 2007. 

(i) If all spoilers are determined to be 

properly stowed, no further action is required 

by this paragraph. 

(ii) If any spoiler is found to be improperly 

stowed (in the up position with the 

speedbrake handle in the down position), 

before further flight, replace the flight spoiler 

actuator with a flight spoiler actuator, having 

part number (P/N) P665A0001–01 or higher 

dash number, in accordance with a method 

approved by the Manager, Seattle Aircraft 

Certification Office (ACO), FAA. The ‘‘Flight 

Spoiler Actuator Removal’’ task and the 

‘‘Flight Spoiler Actuator Installation’’ task in 

Chapter 27–61–51 of the Boeing 737–600/ 

700/800/900 Aircraft Maintenance Manual 

(AMM) are approved methods for the 

replacement (removal and installation) of the 

flight spoiler actuator. 

(2) After any rejected takeoff maneuver, do 

the visual check specified in paragraph (f)(1) 

of this AD. 

(3) After any maintenance action that 

operates the spoiler system, do an 

operational test of the speedbrake control 

system in accordance with a method 

approved by the Manager, Seattle ACO, FAA. 

The ‘‘Speedbrake Control System Operational 

Test’’ specified in Chapter 27–62–00 of the 

Boeing 737–600/700/800/900 AMM is one 

approved method for the operational test of 

the speedbrake control system. If any spoiler 

panel is found to be fully extended with the 

speedbrake handle down, or if any spoiler 

panel is found fully retracted when the 

speedbrake handle is up, before further flight, 

replace the flight spoiler actuator in 

accordance with the actions specified in 

paragraph (f)(1)(ii) of this AD. 

Master Minimum Equipment List Item 

(g) As of the effective date of this AD, the 

Master Minimum Equipment List Item 27–7, 

‘‘Auto Speed Brake System,’’ is no longer 

applicable to Model 737–800 series airplanes 

equipped with an SFP package. 

Optional Terminating Action 

(h) Installation of flight spoiler actuator, P/ 

N P665A0001–01 or higher dash number, in 

all eight flight spoiler positions ends the 

requirements of paragraph (f) of this AD. 

Reporting 

(i) If any spoiler is found to be improperly 

stowed during any visual check required by 

this AD, at the applicable time specified in 

paragraphs (i)(1) and (i)(2) of this AD, report 

the following information electronically to 

Boeing using the established Boeing 

Communications System (BCS): Airplane 

serial number, jam position, spoiler panel 

number or wing position of the spoiler that 

jammed, date of visual check, and flight 

hours accumulated on the airplane. 

(1) For visual checks done before the 

effective date of this AD: Within 7 days after 

the effective date of this AD. 

(2) For visual checks done after the 

effective date of this AD: Within 7 days after 

doing the inspection. 

Parts Installation 

(j) As of the effective date of this AD, no 

person may install a flight spoiler actuator, 

having P/N P665A0001–00, on any airplane. 

Special Flight Permit 

(k) Special flight permits, as described in 

Section 21.197 and Section 21.199 of the 

Federal Aviation Regulations (14 CFR 21.197 

and 21.199), are not allowed. 

Alternative Methods of Compliance 

(AMOCs) 

(l)(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested in accordance with the procedures 

found in 14 CFR 39.19. 


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21086 Federal Register / Vol. 72, No. 82 / Monday, April 30, 2007 / Rules and Regulations 

(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. 

Material Incorporated by Reference 

(m) You must use Boeing 737 Flight Crew 

Operations Manual Bulletin No. TBC–67, 

dated March 5, 2007, to perform the actions 

that are required by this AD, unless the AD 

specifies otherwise. The Director of the 

Federal Register approved the incorporation 

by reference of this document in accordance 

with 5 U.S.C. 552(a) and 1 CFR part 51. 

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/federalregister/cfr/ibr-locations.html. 

Issued in Renton, Washington, on April 18, 

2007. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E7–7850 Filed 4–27–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–27342 Directorate 

Identifier 2007–CE–014–AD; Amendment 

39–15037; AD 2007–09–05] 

RIN 2120–AA64 

Airworthiness Directives; APEX 

Aircraft Model CAP 10 B 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) 

issued by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

A CAP10B aircraft experienced a reduced 

elevator deflection by about 13° due to an 

incorrect routing of the Push To Talk (PTT) 

wire bundle and improperly secured 

connectors which impeded the complete and 

free movement of the control stick. 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective June 

4, 2007. 

On June 4, 2007 the Director of the 

Federal Register approved the 

incorporation by reference of certain 

publications listed in this AD. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

dms.dot.gov or in person at the Docket 

Management Facility, U.S. Department 

of Transportation, 400 Seventh Street, 

SW., Nassif Building, Room PL–401, 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: 

Sarjapur Nagarajan, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 

Locust, Room 301, Kansas City, 

Missouri 64106; telephone: (816) 329–

4145; fax: (816) 329–4090. 

SUPPLEMENTARY INFORMATION: 

Streamlined Issuance of AD 

The FAA is implementing a new 

process for streamlining the issuance of 

ADs related to MCAI. The streamlined 

process will allow us to adopt MCAI 

safety requirements in a more efficient 

manner and will reduce safety risks to 

the public. This process continues to 

follow all FAA AD issuance processes to 

meet legal, economic, Administrative 

Procedure Act, and Federal Register 

requirements. We also continue to meet 

our technical decisionmaking 

responsibilities to identify and correct 

unsafe conditions on U.S.-certificated 

products. 

This AD references the MCAI and 

related service information that we 

considered in forming the engineering 

basis to correct the unsafe condition. 

The AD contains text copied from the 

MCAI and for this reason might not 

follow our plain language principles. 

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 9, 2007 (72 FR 

10624). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

A CAP10B aircraft experienced a reduced 

elevator deflection by about 13° due to an 

incorrect routing of the Push To Talk (PTT) 

wire bundle and improperly secured 

connectors which impeded the complete and 

free movement of the control stick. 

Actions specified in this AD are intended 

to inspect, detect and correct any 

discrepancy on the PTT electrical circuit 

connectors and wires that could lead to a 

reduction of the control stick movements. 

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 FAA policies. 

Any such differences are highlighted in 

a note within the AD. 

Costs of Compliance 

We estimate that this AD will affect 

31 products of U.S. registry. We also 

estimate that it will take about 1 workhour per product to comply with basic 

requirements of this AD. The average 

labor rate is $80 per work-hour. Based 

on these figures, we estimate the cost of 

this AD to the U.S. operators to be 

$2,480 or $80 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 3 work-hours and require parts 

costing $90, for a cost of $330 per 

product. We have no way of 

determining the number of products 

that may need these actions. 

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 


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