37786 Federal Register / Vol. 73, No. 128 / Wednesday, July 2, 2008 / Rules and Regulations 

Models Serial Nos. 

(14) G58 .................................................................................................. TH–2126, TH–2127, TH–2131 through TH–2134, TH–2136, TH–2137, 

TH–2139 through TH–2141, and TH–2143 through TH–2150. 

(15) 77 .................................................................................................... WA–1 through WA–312. 

Unsafe Condition 

(d) This AD results from reports of certain 

circuit breaker toggle switches used in 

various electrical systems through the 

affected airplanes overheating. We are 

proposing this AD to prevent failure of the 

circuit breaker toggle switch, which could 

result in smoke in the cockpit and the 

inability to turn off the switch. 

Compliance 

(e) To address this problem, you must do 

the following, unless already done: 

Actions Compliance Procedures 

(1) Replace all affected circuit breaker toggle 

switches specified in paragraph (c) of this AD 

with an improved circuit breaker toggle 

switch, P/N 35–380132–61 through 35–

380132–113, as applicable.

Within the next 12 months after August 6, 

2008 (the effective date of this AD).

As specified in Hawker Beechcraft Recommended Service Bulletin SB 24–3807, 

Issued: May 2007, and Raytheon Aircraft 

Company Recommended Service Bulletin 

SB 24–3735, Issued: August 2005. 

(2) Do not install a circuit breaker toggle switch 

specified in paragraph (c) of this AD.

Before further flight after the replacement required by paragraph (e)(1) of this AD.Not applicable. 

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: Jose 

Flores, Aviation Safety Engineer, FAA, 

Wichita ACO, 1801 Airport Road, Room 100, 

Wichita, Kansas 67209; telephone: (316) 946–

4132; fax: (316) 946–4107. 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 Hawker Beechcraft 

Recommended Service Bulletin SB 24–3807, 

Issued: May 2007; and Raytheon Aircraft 

Company Recommended Service Bulletin SB 

24–3735, Issued: August 2005, 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 Hawker Beechcraft 

Corporation, 9709 East Central, Wichita, 

Kansas 67291; telephone: (800) 429–5372 or 

(316) 676–3140. 

(3) You may review copies at the FAA, 

Central Region, Office of the Regional 

Counsel, 901 Locust, Kansas City, Missouri 

64106; 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/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Kansas City, Missouri, on June 

16, 2008. 

James E. Jackson, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E8–14090 Filed 7–1–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–0225; Directorate 

Identifier 2007–NM–210–AD; Amendment 

39–15583; AD 2008–13–20] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 757 Airplanes Equipped With 

Rolls Royce RB211–535E Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Boeing Model 757 airplanes equipped 

with Rolls Royce RB211–535E engines. 

This AD requires repetitive inspections 

for signs of damage of the aft hinge 

fittings and attachment bolts of the 

thrust reversers, and related 

investigative and corrective actions if 

necessary. This AD results from reports 

of several incidents of bolt failure at the 

aft hinge fittings of the thrust reversers 

due to, among other things, high 

operational loads. We are issuing this 

AD to prevent failure of the attachment 

bolts and consequent separation of a 

thrust reverser from the airplane during 

flight, which could result in structural 

damage to the airplane. 

DATES: This AD is effective August 6, 

2008. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of August 6, 2008. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, P.O. Box 3707, 

Seattle, Washington 98124–2207. 

Examining the AD Docket 

You may examine the AD docket 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 AD 

docket contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (telephone 800–647–5527) 

is the Document Management Facility, 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Jason Deutschman, Aerospace Engineer, 

Airframe Branch, ANM–120S, Seattle 

Aircraft Certification Office, FAA, 1601 

Lind Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 917–6449; 

fax (425) 917–6590. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an airworthiness 

directive (AD) that would apply to 

certain Boeing Model 757 airplanes 

equipped with Rolls Royce RB211–535E 

engines. That NPRM was published in 

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Federal Register / Vol. 73, No. 128 / Wednesday, July 2, 2008 / Rules and Regulations 37787 

the Federal Register on November 26, 

2007 (72 FR 65903). That NPRM 

proposed to require repetitive 

inspections for signs of damage of the 

aft hinge fittings and attachment bolts of 

the thrust reversers, and related 

investigative and corrective actions if 

necessary. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comments received. 

Request to Include Terminating Action 

Continental Airlines (CAL) and 

Federal Express (FedEx) ask that the 

preventive modification specified in 

Boeing Special Attention Service 

Bulletins 757–54–0049 and 757–54–

0050, both dated July 16, 2007, be 

included in the AD as follows: 

CAL asks that a new paragraph be 

added to clarify that accomplishing the 

preventive modification provided in 

Part III of the above referenced service 

bulletins constitutes terminating action 

for the repetitive inspections required 

by paragraph (f) of the NPRM. 

FedEx states that the referenced 

service bulletins specify that the 

repetitive inspections are no longer 

necessary once the preventive 

modification is accomplished. FedEx 

would like to confirm that 

accomplishing the preventive 

modification will terminate any further 

inspections in the NPRM, and asks that 

we include the terminating action in the 

AD. 

We agree that clarification is 

necessary for the reasons provided; 

therefore, we have added a new 

paragraph (h) to this AD (and reidentified subsequent paragraphs) to 

include optional terminating action for 

paragraph (f) of this AD. 

Request To Clarify Applicability 

FedEx asks that Model 757–200SF 

(special freighter) airplanes be added to 

the applicability specified in paragraph 

(c) of the NPRM. FedEx states that the 

NPRM applies to Model 757–200, 

–200CB, –200PF, and –300 series 

airplanes equipped with Rolls Royce 

RB211–535E engines. FedEx states that 

its airplanes will be modified from the 

Model 757–200 passenger configuration 

to a special freighter configuration. 

FedEx adds that it will submit a 

supplemental type certificate (STC) to 

the FAA to confirm the new 

certification of the airplane after release 

of this AD. 

We do not agree that Model 757–

200SF airplanes should be added to the 

applicability in this AD. The airplanes 

cited by the commenter are legally 

known as ‘‘Model 757–200 airplanes’’ as 

identified on the airplane data plate. 

Even though they might be modified by 

STC and commonly known as ‘‘special 

freighters,’’ these airplanes continue to 

be identified by the type certificated 

model designation. We have made no 

change to the AD in this regard. 

FedEx also asks for clarification of the 

difference between the effectivity 

specified in the concurrent service 

information referenced in paragraph (h) 

of the NPRM and the applicability in the 

NPRM. FedEx states that the concurrent 

service bulletin (Boeing Service Bulletin 

757–54–0015, Revision 3, dated 

September 19, 1996) addresses the 

replacement of older hinge fittings for 

airplanes having line numbers 2 through 

241. 

We provide the following 

clarification. Paragraph (h) of the NPRM 

(changed to paragraph (i) in the final 

rule) requires accomplishing the actions 

in Boeing Service Bulletin 757–54–0015 

prior to or concurrently with 

accomplishing the actions specified in 

Boeing Special Attention Service 

Bulletin 757–54–0049, dated July 16, 

2007. Airplanes having line number 242 

and subsequent have the production 

change installed and are covered by 

paragraph (e) of this AD. The NPRM is 

applicable to airplanes equipped with 

Rolls Royce RB211–535E engines; no 

line numbers are identified. Therefore, 

we have made no change to the AD in 

this regard. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

with the change described previously. 

We also determined that this change 

will not increase the economic burden 

on any operator or increase the scope of 

the AD. 

Costs of Compliance 

There are about 606 airplanes of the 

affected design in the worldwide fleet. 

This AD affects about 295 airplanes of 

U.S. registry. The inspections take about 

2 work hours per airplane, at an average 

labor rate of $80 per work hour. Based 

on these figures, the estimated cost of 

the AD for U.S. operators is $47,200, or 

$160 per airplane, per inspection cycle. 

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 

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. 

You can find our regulatory 

evaluation and the estimated costs of 

compliance in the AD Docket. 

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: 

2008–13–20 Boeing: Amendment 39–15583. 

Docket No. FAA–2007–0225; Directorate 

Identifier 2007–NM–210–AD. 

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37788 Federal Register / Vol. 73, No. 128 / Wednesday, July 2, 2008 / Rules and Regulations 

Effective Date 

(a) This airworthiness directive (AD) is 

effective August 6, 2008. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Boeing Model 757–

200, –200CB, –200PF, and –300 series 

airplanes, certificated in any category; 

equipped with Rolls Royce RB211–535E 

engines. 

Unsafe Condition 

(d) This AD results from reports of several 

incidents of bolt failure at the aft hinge 

fittings of the thrust reversers due to, among 

other things, high operational loads. We are 

issuing this AD to prevent failure of the 

attachment bolts and consequent separation 

of a thrust reverser from the airplane during 

flight, which could result in structural 

damage to 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. 

Repetitive Inspections/Investigative and 

Corrective Actions 

(f) At the time specified in paragraph 1.E. 

‘‘Compliance,’’ of Boeing Special Attention 

Service Bulletin 757–54–0049 or 757–54–

0050, both dated July 16, 2007, as applicable, 

except as provided by paragraph (g) of this 

AD: Do a detailed inspection for signs of 

damage of the aft hinge fittings and 

attachment bolts of the thrust reversers by 

doing all the actions, including all applicable 

related investigative and corrective actions, 

as specified in the Accomplishment 

Instructions of the applicable service 

bulletin. Do all applicable related 

investigative and corrective actions at the 

time specified in paragraph 1.E., 

‘‘Compliance,’’ of the applicable service 

bulletin. If any damage is found and the 

service bulletins specify to contact Boeing for 

appropriate action: Before further flight, 

repair using a method approved in 

accordance with the procedures specified in 

paragraph (k) of this AD. 

(g) Where Boeing Special Attention Service 

Bulletins 757–54–0049 and 757–54–0050, 

both dated July 16, 2007, specify compliance 

times relative to the date on the service 

bulletin, this AD requires compliance within 

the specified compliance time after the 

effective date of this AD. 

Optional Terminating Action 

(h) Accomplishing the preventive 

modification specified in Boeing Special 

Attention Service Bulletin 757–54–0049 or 

757–54–0050, both dated July 16, 2007, 

terminates the repetitive inspections required 

by paragraph (f) of this AD. 

Concurrent Actions 

(i) Prior to or concurrently with 

accomplishing the actions specified in 

Boeing Special Attention Service Bulletin 

757–54–0049, dated July 16, 2007, 

accomplish the replacement specified in 

Boeing Service Bulletin 757–54–0015, 

Revision 3, dated September 19, 1996. 

(j) Actions accomplished before the 

effective date of this AD in accordance with 

Boeing Service Bulletin 757–54–0015, dated 

February 16, 1989; Revision 1, dated 

December 20, 1990; or Revision 2, dated 

April 21, 1994 are considered acceptable for 

compliance with the corresponding actions 

specified in paragraph (i) of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(k)(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. 

(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) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD, if it is approved by an 

Authorized Representative for the Boeing 

Commercial Airplanes Delegation Option 

Authorization Organization who has been 

authorized by the Manager, Seattle ACO, to 

make those findings. For a repair method to 

be approved, the repair must meet the 

certification basis of the airplane, and the 

approval must specifically refer to this AD. 

Material Incorporated by Reference 

(l) You must use the Boeing service 

information contained in Table 1 of this AD 

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 Boeing Commercial 

Airplanes, P.O. Box 3707, Seattle, 

Washington 98124–2207. 

(3) You may review copies of the service 

information that is incorporated by reference 

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/ 

code_of_federal_regulations/ 

ibr_locations.html. 

TABLE 1.—MATERIAL INCORPORATED BY REFERENCE

Service information Revision Date 

Boeing Special Attention Service Bulletin 757–54–0015 ................................................................ 3 ................................ September 19, 1996. 

Boeing Special Attention Service Bulletin 757–54–0049 ................................................................ Original ...................... July 16, 2007. 

Boeing Service Bulletin 757–54–0050 ............................................................................................ Original ...................... July 16, 2007. 

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Federal Register / Vol. 73, No. 128 / Wednesday, July 2, 2008 / Rules and Regulations 37789 

Issued in Renton, Washington, on June 8, 

2008. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E8–14190 Filed 7–1–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0293; Directorate 

Identifier 2007–NM–287–AD; Amendment 

39–15582; AD 2008–13–19] 

RIN 2120–AA64 

Airworthiness Directives; ATR Model 

ATR42–200, –300, –320, –500 

Airplanes; and Model ATR72–101, 

–201, –102, –202, –211, –212, and 

–212A 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: 

A recent incident evidenced that some 

failures of the Pitot probe heating resistance 

may not be seen by the low current detection 

system on aircraft not equipped with [ATR] 

modification 05469 * * *. In some 

conditions, an out of tolerance resistance, 

failing to provide a proper Pitot probe deicing could not be detected. 

* * * * * 

The unsafe condition is that 

undetected icing of the pitot probe 

could produce incorrect airspeed 

readings, which could lead to loss of 

control of the airplane. We are issuing 

this AD to require actions to correct the 

unsafe condition on these products. 

DATES: This AD becomes effective 

August 6, 2008. The Director of the 

Federal Register approved the 

incorporation by reference of certain 

publications listed in this AD as of 

August 6, 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: Tom 

Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 227–1137; 

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 March 13, 2008 (73 FR 

13496). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

A recent incident evidenced that some 

failures of the Pitot probe heating resistance 

may not be seen by the low current detection 

system on aircraft not equipped with [ATR] 

modification 05469 (SB (Service Bulletin) 

ATR42–30–0072 or ATR72–30–1042). In 

some conditions, an out of tolerance 

resistance, failing to provide a proper Pitot 

probe de-icing could not be detected. 

To address this unsafe condition, this 

Airworthiness Directive (AD) requires 

repetitive verification of the Pitot probes’

resistance and replacement of any defective 

probes, and ultimate replacement of the three 

low current sensors for Captain, First Officer 

and Standby Pitot probes. 

The unsafe condition is that 

undetected icing of the pitot probe 

could produce incorrect airspeed 

readings, which could lead to loss of 

control of the airplane. 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. 

Actions Since the NPRM Was Issued 

ATR has issued revisions to two of the 

service information documents 

identified in the NPRM: Avions de 

Transport Regional Service Bulletins 

ATR42–30–0074 and ATR72–30–1044, 

both Revision 01, both dated September 

26, 2007. We have changed paragraphs 

(f)(1) and (h) accordingly, and added 

paragraph (f)(3) to give credit for actions 

done per the original versions of those 

service bulletins. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously. 

We determined that these changes will 

not increase the economic burden on 

any operator or increase the scope of the 

AD. 

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 51 products of U.S. registry. We 

also estimate that it will take about 4 

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 $1,880 

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 

$112,200, or $2,200 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. 

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