17882 Federal Register / Vol. 75, No. 67 / Thursday, April 8, 2010 / Proposed Rules 

Alternative Methods of Compliance 

(AMOCs) 

(m)(1) 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: T.N. 

Baktha, Aerospace Engineer, Airframe 

Branch, ACE–118W, FAA, Wichita ACO, 

1801 Airport Road, Room 100, Mid-Continent 

Airport, Wichita, Kansas 67209; telephone 

(316) 946–4155; fax (316) 946–4107. 

(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 principal maintenance inspector 

(PMI) or principal avionics inspector (PAI), 

as appropriate, or lacking a principal 

inspector, your local Flight Standards District 

Office. The AMOC approval letter must 

specifically reference this AD. 

Issued in Renton, Washington, on April 1, 

2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–7943 Filed 4–7–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0379; Directorate 

Identifier 2009–NM–210–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 737–300, –400, and 

–500 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to 

supersede an existing airworthiness 

directive (AD) that applies to all Model 

737–300, –400, and –500 series 

airplanes. The existing AD currently 

requires inspecting to determine if 

certain carriage spindles are installed, 

repetitive inspections for corrosion and 

indications of corrosion on affected 

carriage spindles, and if necessary, 

related investigative and corrective 

actions. The existing AD also provides 

an optional terminating action. This 

proposed AD would mandate the 

optional terminating action, which 

would eliminate the need for the 

repetitive inspections. The proposed AD 

results from reports of corrosion found 

on carriage spindles that are located on 

the outboard trailing edge flaps. We are 

proposing this AD to detect and correct 

corrosion of the carriage spindle, which 

could result in fracture. Fracture of both 

the inboard and outboard carriage 

spindles, in the forward ends through 

the large diameters, on a flap, could 

adversely affect the airplane’s continued 

safe flight and landing. 

DATES: We must receive comments on 

this proposed AD by May 24, 2010. 

ADDRESSES: You may send comments by 

any of the following methods: 

• 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. 

For service information identified in 

this proposed AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, Washington 98124– 

2207; telephone 206–544–5000, 

extension 1; fax 206–766–5680; e-mail 

me.boecom@boeing.com; Internet 

https://www.myboeingfleet.com. You 

may review copies of the referenced 

service information at the FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington. 

For information on the availability of 

this material at the FAA, call 425–227– 

1221. 

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 proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(telephone 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Nancy Marsh, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 917–6440; fax (425) 917–6590. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2010–0379; Directorate Identifier 

2009–NM–210–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD because 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 

about this proposed AD. 

Discussion 

On October 26, 2009, we issued AD 

2009–23–10, Amendment 39–16084 (74 

FR 57564, November 9, 2009), for all 

Model 737–300, –400, and –500 series 

airplanes. That AD requires inspecting 

to determine if certain carriage spindles 

are installed, repetitive inspections for 

corrosion and indications of corrosion 

on affected carriage spindles, and if 

necessary, related investigative and 

corrective actions. That AD also 

provides an optional terminating action. 

That AD resulted from reports of 

corrosion found on carriage spindles 

that are located on the outboard trailing 

edge flaps. We issued that AD to detect 

and correct corrosion of the carriage 

spindle, which could result in fracture. 

Fracture of both the inboard and 

outboard carriage spindles, in the 

forward ends through the large 

diameters, on a flap, could adversely 

affect the airplane’s continued safe 

flight and landing. 

Actions Since Existing AD Was Issued 

The preamble to AD 2009–23–10 

explains that we consider the 

requirements ‘‘interim action’’ and were 

considering further rulemaking. We now 

have determined that further 

rulemaking is indeed necessary, and 

this proposed AD follows from that 

determination. 

Boeing Commercial Airplanes has 

received an Organization Designation 

Authorization (ODA), which replaces 

their previous designation as a 

Delegation Option Authorization (DOA) 

holder. We have revised paragraph (l)(3) 

of this AD to delegate the authority to 

approve an alternative method of 


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Federal Register / Vol. 75, No. 67 / Thursday, April 8, 2010 / Proposed Rules 17883 

compliance for any repair required by 

this AD to the Boeing Commercial 

Airplanes ODA. 

FAA’s Determination and Requirements 

of the Proposed AD 

We have evaluated all pertinent 

information and identified an unsafe 

condition that is likely to develop on 

other airplanes of the same type design. 

For this reason, we are proposing this 

AD, which would supersede AD 2009– 

23–10 and would retain the 

requirements of the existing AD. This 

proposed AD would also mandate the 

optional terminating action, which 

would eliminate the need for the 

repetitive inspections. 

Costs of Compliance 

There are about 482 airplanes of the 

affected design in the worldwide fleet. 

This proposed AD would affect about 

150 airplanes of U.S. registry. 

The inspection that is required by AD 

2009–23–10 and retained in this 

proposed AD takes about 2 work hours 

per airplane, at an average labor rate of 

$85 per work hour. Based on these 

figures, the estimated cost of the 

currently required inspection is $170 

per airplane, per inspection cycle. 

The replacement of each affected 

carriage spindle that is proposed in this 

AD would take about 17 work hours per 

spindle (4 spindles per airplane), at an 

average labor rate of $85 per work hour. 

Required parts cost would be provided 

under warranty. Based on these figures, 

the estimated cost of the replacement 

specified in this proposed AD for U.S. 

operators is up to $5,780, or $1,445 per 

carriage spindle or up to $867,000. 

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 have determined that this 

proposed AD would not have federalism 

implications under Executive Order 

13132. This proposed AD would 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 the proposed regulation: 

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 proposed AD and placed it in the 

AD docket. See the ADDRESSES section 

for a location to examine the regulatory 

evaluation. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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 

removing Amendment 39–16084 (74 FR 

57564, November 9, 2009) and adding 

the following new AD: 

The Boeing Company: Docket No. FAA– 

2010–0379; Directorate Identifier 2009– 

N–210–AD. 

Comments Due Date 

(a) The FAA must receive comments on 

this AD action by May 24, 2010. 

Affected ADs 

(b) This AD supersedes AD 2009–23–10, 

Amendment 39–16084. 

Applicability 

(c) This AD applies to all The Boeing 

Company Model 737–300, –400, and –500 

series airplanes, certificated in any category. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 57: Wings. 

Unsafe Condition 

(e) This AD results from reports of 

corrosion found on carriage spindles that are 

located on the outboard trailing edge flaps. 

The Federal Aviation Administration is 

issuing this AD to detect and correct 

corrosion of the carriage spindle, which 

could result in fracture. Fracture of both the 

inboard and outboard carriage spindles, in 

the forward ends through the large diameters, 

on a flap, could adversely affect the 

airplane’s continued safe flight and landing. 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

RESTATEMENT OF REQUIREMENTS OF 

AD 2008–15–05, AMENDMENT 39–15617: 

Inspection To Determine Affected Carriage 

Spindle 

(g) For all airplanes: Within 30 days after 

August 5, 2008 (the effective date of AD 

2008–15–05), inspect the carriage subassembly to determine whether an affected 

carriage spindle with a high velocity oxy-fuel 

(HVOF) thermal coating is installed, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–57A1304, dated June 2, 2008. A review 

of airplane maintenance records is acceptable 

in lieu of this inspection if the part number 

and/or serial number of the carriage can be 

conclusively determined from that review. If 

no affected carriage spindle is installed, no 

further action is required by this paragraph. 

Repetitive Inspections, Related Investigative 

Actions, and Corrective Action 

(h) For airplanes on which any affected 

carriage spindle was determined to be 

installed in accordance with Boeing Alert 

Service Bulletin 737–57A1304, dated June 2, 

2008, as of August 5, 2008; and the spindle 

is identified in Table 2 of Boeing Service 

Bulletin 737–57A1304, Revision 1, dated 

August 11, 2009: At the later of the times 

specified in paragraphs (h)(1) and (h)(2) of 

this AD, do a detailed inspection (or, as an 

option for the forward end of the spindle 

only, a borescope inspection technique may 

be used) of the spindle for corrosion and 

potential indications of corrosion of the 

carriage spindle, and do all applicable related 

investigative and corrective actions, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–57A1304, dated June 2, 2008; or Boeing 

Service Bulletin 737–57A1304, Revision 1, 

dated August 11, 2009. Do all applicable 

related investigative and corrective actions 

before further flight. Repeat the detailed 

inspection (or, as an option for the forward 

end of the spindle only, the borescope 

inspection) and certain related investigative 

actions (i.e., the gap-check or optional nondestructive test (NDT) ultrasonic inspection) 

at the applicable compliance times specified 

in paragraph 1.E. of Boeing Alert Service 

Bulletin 737–57A1304, dated June 2, 2008; or 


sroberts on DSKD5P82C1PROD with PROPOSALS
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Boeing Service Bulletin 737–57A1304, 

Revision 1, dated August 11, 2009. 

(1) Within 30 days after August 5, 2008. 

(2) Within 90 days after the installation of 

a new HVOF-coated spindle. 

Note 1: Boeing Alert Service Bulletin 737– 

57A1304, dated June 2, 2008; and Boeing 

Service Bulletin 737–57A1304, Revision 1, 

dated August 11, 2009; reference Boeing 

Alert Service Bulletin 737–57A1277, 

Revision 1, dated November 25, 2003; for 

further guidance on accomplishing the 

related investigative actions. 

RESTATEMENT OF REQUIREMENTS OF 

AD 2009–23–10, AMENDMENT 39–16084: 

Repetitive Inspections, Related Investigative 

Actions, and Corrective Action for Certain 

Airplanes 

(i) For airplanes on which a carriage 

spindle having a serial number identified in 

Table 3 of Appendix A of Boeing Service 

Bulletin 737–57A1304, Revision 1, dated 

August 11, 2009, is installed: At the latest of 

the times specified in paragraphs (i)(1), (i)(2), 

and (i)(3) of this AD, as applicable, do a 

detailed inspection (or, as an option for the 

forward end of the spindle only, a borescope 

inspection technique may be used) of the 

spindle for corrosion and potential 

indications of corrosion of the carriage 

spindle, and do all applicable related 

investigative and corrective actions, in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 737– 

57A1304, Revision 1, dated August 11, 2009. 

Do all applicable related investigative and 

corrective actions before further flight. 

Repeat the detailed inspection (or, as an 

option for the forward end of the spindle 

only, the borescope inspection) and related 

investigative actions (i.e., the gap-check or 

optional NDT ultrasonic inspection) at the 

applicable compliance times specified in 

paragraph 1.E. of Boeing Service Bulletin 

737–57A1304, Revision 1, dated August 11, 

2009. 

(1) Within 30 days after November 24, 2009 

(the effective date of AD 2009–23–10). 

(2) Within 90 days after the installation of 

a new HVOF-coated spindle identified in 

Table 3 of Appendix A of Boeing Service 

Bulletin 737–57A1304, Revision 1, dated 

August 11, 2009. 

(3) Within 90 days after doing an 

inspection in accordance with Boeing Alert 

Service Bulletin 737–57A1304, dated June 2, 

2008. 

Parts Installation 

(j) As of August 5, 2008, an HVOF-coated 

spindle without an ‘R’ suffix on the serial 

number may be installed on an airplane 

provided the actions required by paragraph 

(h) or (i) of this AD, as applicable, are done 

on that spindle. 

NEW REQUIREMENTS OF THIS AD: 

Terminating Action 

(k) Within 48 months after the effective 

date of this AD: Replace any HVOF-coated 

carriage spindle having a serial number 

identified in Table 2 or 3 of Appendix A of 

Boeing Service Bulletin 737–57A1304, 

Revision 1, dated August 11, 2009, with a 

non-HVOF coated carriage spindle, or with a 

serviceable HVOF-coated carriage spindle 

with an ‘R’ suffix on the serial number, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–57A1304, dated June 2, 2008; or Boeing 

Service Bulletin 737–57A1304, Revision 1, 

dated August 11, 2009. Replacing all affected 

carriage spindles terminates the repetitive 

inspections required by this AD. 

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 using the procedures found in 14 

CFR 39.19. Send information to ATTN: 

Nancy Marsh, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle ACO, 1601 

Lind Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 917–6440; fax 

(425) 917–6590. Or, e-mail information to 

9-ANM-Seattle-ACO-AMOCRequests@faa.gov. 

(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 principal maintenance inspector 

(PMI) or principal avionics inspector (PAI), 

as appropriate, or lacking a principal 

inspector, your local Flight Standards District 

Office. The AMOC approval letter must 

specifically reference this AD. 

(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 the 

Boeing Commercial Airplanes Organization 

Delegation Authorization (ODA) that 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. 

Issued in Renton, Washington, on April 1, 

2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–7944 Filed 4–7–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0375; Directorate 

Identifier 2010–NM–014–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Model CL–600–2B19 (Regional Jet 

Series 100 & 440) Airplanes; Model 

CL–600–2C10 (Regional Jet Series 700, 

701, & 702) Airplanes; Model CL–600– 

2D15 (Regional Jet Series 705) and 

Model CL–600–2D24 (Regional Jet 

Series 900) Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above. This proposed 

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: Following five reported 

cases of balance washer screw failure on 

similar ADGs [air-driven generators]/ 

ram air turbines installed on other 

aircraft types, investigation by Hamilton 

Sundstrand determined that a specific 

batch of the screws had a 

metallographic non-conformity that 

increased their susceptibility to brittle 

fracture. Failure of a balance washer 

screw can result in loss of the related 

balance washer, with consequent 

turbine imbalance. Such imbalance 

could potentially result in ADG 

structural failure (including blade 

failure), loss of ADG electrical power 

and structural damage to the aircraft 

and, if deployment was activated by a 

dual engine shutdown, could also result 

in loss of hydraulic power for the flight 

controls [and consequent reduced 

ability of the flightcrew to maintain the 

safe flight and landing of the airplane]. 

The proposed AD would require 

actions that are intended to address the 

unsafe condition described in the MCAI. 

DATES: We must receive comments on 

this proposed AD by May 24, 2010. 

ADDRESSES: You may send comments by 

any of the following methods: 

• 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– 


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