16648 Federal Register / Vol. 75, No. 63 / Friday, April 2, 2010 / Rules and Regulations 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective May 7, 2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Bombardier, Inc. 

Model BD–100–1A10 (Challenger 300) 

airplanes, certificated in any category, serial 

numbers 20002 through 20153 inclusive. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 32: Landing gear. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

There has been an incident during a 

production flight test where the proximitysensor electronic unit (PSEU) failed. This 

resulted in unannunciated loss of: 

• Wheel brakes below 10 knots; 

• Thrust reverser; 

• Nose wheel steering; and 

• Auto-deployment of the multi-function 

spoilers. 

A similar condition, if not corrected, may 

result in reduced controllability of the 

aircraft upon landing and possible overrun of 

the runway. 

The original issue of this directive 

mandated the introduction of non-normal 

procedures to the airplane flight manual 

(AFM) as an interim corrective action to 

address PSEU failures. 

Revision 1 of this directive amends the 

aircraft applicability and introduces a note 

providing terminating action, for use at 

operator discretion, if the aircraft has 

incorporated a PSEU with software version 

12 in accordance with Bombardier Service 

Bulletin (SB) 100–32–12. 

Actions and Compliance 

(f) Unless already done, within 14 days 

after the effective date of this AD: Revise the 

Limitations Section of the Bombardier 

Challenger 300 AFM, CSP 100–1, to include 

the information in Bombardier Temporary 

Revision TR–39, dated March 2, 2005, as 

specified in the temporary revision. This 

temporary revision introduces a procedure 

for ‘‘PROX SYS FAULT (A)’’ and modifies the 

‘‘WOW FAIL (C)’’ and ‘‘GEAR SYS FAIL (C)’’ 

procedures. 

Note 1: This may be done by inserting a 

copy of Bombardier Temporary Revision TR– 

39, dated March 2, 2005, in the AFM. When 

this temporary revision has been included in 

general revisions of the AFM, the general 

revisions may be inserted in the AFM, 

provided the relevant information in the 

general revision is identical to that in 

Bombardier Temporary Revision TR–39, 

dated March 2, 2005. 

Note 2: If the aircraft has incorporated a 

PSEU, part number (P/N) 30227–0401, 

30227–0402, or 30227–0403, with software 

version 12, installed in accordance with 

Bombardier Service Bulletin 100–32–12, 

dated June 4, 2007, it is permissible to follow 

the revised AFM procedures included in 

Bombardier Temporary Revision TR–46, 

dated March 27, 2008, in lieu of using 

Bombardier Temporary Revision TR–39, 

dated March 2, 2005, specified in paragraph 

(f) of this AD. 

FAA AD Differences 

Note 3: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(g) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

Certification Office (ACO), ANE–170, 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: 

Program Manager, Continuing Operational 

Safety, FAA, New York ACO, 1600 Stewart 

Avenue, Suite 410, Westbury, New York 

11590; telephone 516–228–7300; fax 516– 

794–5531. 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. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, under the 

provisions of the Paperwork Reduction Act 

(44 U.S.C. 3501 et seq.), the Office of 

Management and Budget (OMB) has 

approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(h) Refer to MCAI Transport Canada Civil 

Aviation Airworthiness Directive CF–2005– 

12R1, dated December 23, 2008; and 

Bombardier Temporary Revision TR–39, 

dated March 2, 2005; for related information. 

Material Incorporated by Reference 

(i) You must use Bombardier Temporary 

Revision TR–39, dated March 2, 2005, to the 

Bombardier Challenger 300 Airplane Flight 

Manual, CSP 100–1, 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 Bombardier, Inc., 400 CoˆteVertu Road West, Dorval, Que ́bec H4S 1Y9, 

Canada; telephone 514–855–5000; fax 514– 

855–7401; e-mail 

thd.crj@aero.bombardier.com; Internet 

http://www.bombardier.com. 

(3) You may review copies of the 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. 

(4) You may also review copies of the 

service information that is incorporated by 

reference 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 Renton, Washington, on March 

19, 2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–6785 Filed 4–1–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0230; Directorate 

Identifier 2010–NM–071–AD; Amendment 

39–16250; AD 2010–06–51] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 737–600, –700, –700C, 

–800, –900, and –900ER 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) 

2010–06–51 that was sent previously to 

all known U.S. owners and operators of 

The Boeing Company Model 737–600, 

–700, –700C, –800, –900, and –900ER 

series airplanes by individual notices. 

This AD requires doing a detailed 

inspection of the inboard and outboard 

aft attach lugs of the left and right 

elevator control tab mechanisms for 

gaps between the swage ring and the aft 

attach lug, and between the spacer and 

the aft attach lug; trying to move or 

rotate the spacer using hand pressure; 

and replacing any discrepant elevator 

tab control mechanism, including 

performing the detailed inspection on 

the replacement part before and after 

installation. This AD is prompted by a 

report of failure of the aft attach lugs on 

the left elevator tab control mechanism, 

which resulted in severe elevator 

vibration. We are issuing this AD to 

detect and correct a loose bearing in the 

aft lug of the elevator tab control 


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mechanism, which could result in 

unwanted elevator and tab vibration. 

The consequent structural failure of the 

elevator or horizontal stabilizer could 

result in loss of aircraft control and 

structural integrity. 

DATES: This AD becomes effective April 

7, 2010 to all persons except those 

persons to whom it was made 

immediately effective by emergency AD 

2010–06–51, issued March 12, 2010, 

which contained the requirements of 

this amendment. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of April 7, 2010. 

We must receive comments on this 

AD by May 17, 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 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. 

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 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: 

Kelly McGuckin, Aerospace Engineer, 

Systems and Equipment Branch, ANM– 

130S, FAA, Seattle ACO, 1601 Lind 

Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 917–6490; 

fax (425) 917–6590. 

SUPPLEMENTARY INFORMATION: On March 

12, 2010, we issued emergency AD 

2010–06–51, which applies to all The 

Boeing Company Model 737–600, –700, 

–700C, –800, –900, and –900ER series 

airplanes. 

Background 

The FAA received a report of failure 

of the aft attach lugs on the left elevator 

tab control mechanism, which resulted 

in severe elevator vibration. The 

flightcrew diverted from the intended 

route and made an uneventful landing. 

Subsequent investigation revealed 

extensive damage to the elevator tab 

control system. Severe vibration in this 

attach point is suspected of allowing 

rapid wear of the joint, and resulted in 

failure of the attach lugs. This 

condition, if not corrected, could result 

in a loss of aircraft control and 

structural integrity. 

Relevant Service Information 

We have reviewed Boeing Alert 

Service Bulletin 737–27A1296, dated 

March 12, 2010. The service bulletin 

describes procedures for a detailed 

inspection to detect discrepancies of the 

inboard and outboard aft attach lugs of 

the elevator tab control mechanism. 

Discrepancies include movement or 

rotation of the spacer, and gaps between 

the swage ring and the aft attach lug or 

between the spacer and the aft attach 

lug. The service bulletin describes 

procedures for replacing any discrepant 

elevator tab control mechanism, 

including performing the detailed 

inspection on the replacement part 

before and after installation. For certain 

airplanes, the compliance time for the 

inspection is 12 or 30 days, depending 

on airplane line number, total 

accumulated flight cycles, and approval 

for operation under extended twin 

operations (ETOPS). 

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 2010–06–51 to 

detect and correct a loose bearing in the 

aft lug of the elevator tab control 

mechanism, which could result in 

unwanted elevator and tab vibration. 

The consequent structural failure of the 

elevator or horizontal stabilizer could 

result in loss of aircraft control and 

structural integrity. The AD requires 

accomplishing the actions specified in 

the service information previously 

described, except as described in 

‘‘Differences Between this AD and the 

Service Bulletin.’’ This AD also requires 

reporting the inspection results to 

Boeing. 

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 12, 2010, to all 

known U.S. owners and operators of 

The Boeing Company Model 737–600, 

–700, –700C, –800, –900, and –900ER 

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 Bulletin 

The effectivity of Boeing Alert Service 

Bulletin 737–27A1296, dated March 12, 

2010, includes all Model 737–600, –700, 

–700C, –800, –900, and –900ER series 

airplanes. The inspection requirements 

of this AD, however, affect only those 

airplanes subject to a short compliance 

time (within 12 or 30 days). Because the 

suspect components may be installed as 

replacements on all airplanes subject to 

this AD, paragraph (l) of this AD 

requires that the part be inspected 

before and after installation. We may 

consider superseding this AD to apply 

the inspection requirements to the 

remaining airplanes, which would be 

subject to a longer compliance time that 

would allow enough time to provide 

notice and opportunity for prior public 

comment on the merits of the inspection 

for these airplanes. 

Interim Action 

This AD is considered to be interim 

action. The inspection reports that are 

required by this AD will enable the 

manufacturer to obtain better insight 

into the nature, cause, and extent of the 

issue, and eventually to develop final 

action to address the unsafe condition. 

Once final action has been identified, 

we might consider further rulemaking. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not provide you with notice and 

an opportunity to provide your 

comments before it becomes effective. 

However, we invite you to send any 

written data, views, or arguments about 

this AD. Send your comments to an 

address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2010–0230; Directorate Identifier 2010– 

NM–071–AD’’ at the beginning of your 

comments. We specifically invite 


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16650 Federal Register / Vol. 75, No. 63 / Friday, April 2, 2010 / Rules and Regulations 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this AD. We will consider all 

comments received by the closing date 

and may amend this 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 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 

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): 

2010–06–51 The Boeing Company: 

Amendment 39–16250. Docket No. 

FAA–2010–0230; Directorate Identifier 

2010–NM–071–AD. 

Effective Date 

(a) This AD becomes effective April 7, 

2010, to all persons except those persons to 

whom it was made immediately effective by 

emergency AD 2010–06–51, issued on March 

12, 2010, which contained the requirements 

of this amendment. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to all The Boeing 

Company Model 737–600, –700, –700C, 

–800, –900, and –900ER series airplanes; 

certificated in any category. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 27: Flight controls. 

Unsafe Condition 

(e) This AD results from a report of failure 

of the aft attach lugs on the left elevator tab 

control mechanism, which resulted in severe 

elevator vibration. The Federal Aviation 

Administration is issuing this AD to detect 

and correct a loose bearing in the aft lug of 

the elevator tab control mechanism, which 

could result in unwanted elevator and tab 

vibration. The consequent structural failure 

of the elevator or horizontal stabilizer could 

result in loss of aircraft control and structural 

integrity. 

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. 

Inspection and Corrective Action 

(g) For Groups 1, 2, and 3; and Group 4, 

Configuration 2; as identified in Boeing Alert 

Service Bulletin 737–27A1296, dated March 

12, 2010: At the applicable time specified in 

paragraph 1.E. Compliance of Boeing Alert 

Service Bulletin 737–27A1296, dated March 

12, 2010, except as required by paragraph (i) 

of this AD, do a detailed inspection of the 

inboard and outboard aft attach lugs of the 

left and right elevator control tab 

mechanisms for gaps between the swage ring 

and the aft attach lug, and between the spacer 

and the aft attach lug; and try to move or 

rotate the spacer using hand pressure, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–27A1296, dated March 12, 2010. 

(h) If, during accomplishment of the 

actions required by paragraph (g) of this AD, 

any gap is found between the swage ring and 

the aft attach lug, or between the spacer and 

the aft attach lug; or if the spacer moves or 

rotates: Before further flight, do the actions 

required by paragraphs (h)(1) and (h)(2) of 

this AD, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–27A1296, dated March 

12, 2010. 

(1) Inspect the replacement elevator tab 

control mechanism for discrepancies, as 

specified in paragraph (g) of this AD; and, if 

no discrepancy is found, install the 

replacement elevator tab control mechanism. 

(2) Re-inspect the installed elevator tab 

control mechanism, as required by paragraph 

(g) of this AD. 

Exception to Service Bulletin Specifications 

(i) Where Boeing Alert Service Bulletin 

737–27A1296, dated March 12, 2010, 

specifies a compliance time after the date of 

the original issue of the service bulletin, this 

AD requires compliance within the specified 

compliance time after the effective date of 

this AD. 

Inspection Done According to Multi 

Operator Message (MOM) 

(j) An inspection done before the effective 

date of this AD according to Boeing Multi 

Operator Message Number MOM–MOM–10– 

0159–01B, dated March 10, 2010, is 

considered acceptable for compliance with 

the corresponding inspection specified in 

paragraph (g) of this AD. 

Reporting 

(k) At the applicable time specified in 

paragraph (k)(1) or (k)(2) of this AD: Submit 

a report of the findings (both positive and 

negative) of the inspections required by 

paragraph (g) of this AD to Boeing 

Commercial Airplanes Group, Attention: 

Manager, Airline Support, e-mail: 

rse.boecom@boeing.com. The report must 

include the inspection results including a 

description of any discrepancies found, the 

airplane line number, and the number of 

flight cycles and flight hours accumulated on 

the airplane. Under the provisions of the 

Paperwork Reduction Act (44 U.S.C. 3501 et 

seq.), the Office of Management and Budget 

(OMB) has approved the information 

collection requirements contained in this AD 

and has assigned OMB Control Number 

2120–0056. 

(1) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 10 days after the inspection. 

(2) If the inspection was done before the 

effective date of this AD: Submit the report 


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Federal Register / Vol. 75, No. 63 / Friday, April 2, 2010 / Rules and Regulations 16651 

within 10 days after the effective date of this 

AD. 

Parts Installation 

(l) For all airplanes: As of the effective date 

of this AD, no person may install an elevator 

tab control mechanism, part number 

251A2430–( ), on any airplane, unless the 

mechanism has been inspected before and 

after installation, in accordance with the 

requirements of paragraph (g) of this AD, and 

no discrepancies have been found. 

Special Flight Permit 

(m) 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) 

(n)(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: Kelly 

McGuckin, Aerospace Engineer, Systems and 

Equipment Branch, ANM–130S, FAA, Seattle 

ACO, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 425– 

917–6490; fax 425–917–6590. Information 

may be e-mailed to 9-ANM-Seattle-ACOAMOC-Requests@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 refer to 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 

Designation 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. 

Material Incorporated by Reference 

(o) You must use Boeing Alert Service 

Bulletin 737–27A1296, dated March 12, 

2010, 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, 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. 

(3) You may review copies of the 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. 

(4) You may also review copies of the 

service information that is incorporated by 

reference 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 Renton, Washington, on March 

18, 2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–6786 Filed 4–1–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0684; Directorate 

Identifier 2008–NM–149–AD; Amendment 

39–16247; AD 2010–07–03] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 747–200C and –200F 

Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD), 

which applies to certain Model 747– 

200C and –200F series airplanes. That 

AD currently requires repetitive 

inspections to find fatigue cracking in 

the floor panel attachment fastener 

holes of the upper chord of certain 

upper deck floor beams in Section 41 

(i.e., body station 520 and forward), and 

repair if necessary. The existing AD also 

provides optional modifications, which 

extend the threshold for initiating 

certain repetitive inspections. This new 

AD requires additional repetitive 

inspections to find fatigue cracking in 

the floor panel attachment fastener 

holes of the upper chord of certain other 

upper deck floor beams in Section 41 

and Section 42 (i.e., aft of body station 

520); repetitive inspections to find 

fatigue cracking in the permanent 

fastener holes of the upper chord of 

certain upper deck floor beams in 

Section 41; and related investigative and 

corrective actions. This new AD also 

provides a new optional modification, 

which terminates certain repetitive 

inspections. This AD results from new 

reports of cracking in the upper chord 

of the upper deck floor beams in 

Sections 41 and 42, and new analysis 

that shows the permanent fastener holes 

of the upper chord of certain upper deck 

floor beams in Section 41 are also 

susceptible to fatigue cracking. We are 

issuing this AD to detect and correct 

cracking in the upper chord of the upper 

deck floor beams. Such cracking could 

extend and sever the floor beams, which 

could result in rapid decompression and 

loss of controllability of the airplane. 

DATES: This AD becomes effective May 

7, 2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of May 7, 2010. 

ADDRESSES: For service information 

identified in this 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. 

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 Docket 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: Ivan 

Li, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 917–6437; 

fax (425) 917–6590. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that 

supersedes AD 2006–08–02, amendment 

39–14556 (70 FR 18618, April 12, 2006). 

The existing AD applies to certain 

Model 747–200C and –200F series 

airplanes. That NPRM was published in 

the Federal Register on August 12, 2009 

(74 FR 40529). That NPRM proposed to 

continue to require repetitive 

inspections to find fatigue cracking in 

the floor panel attachment fastener 


wwoods2 on DSK1DXX6B1PROD with RULES_PART 1