32414 Federal Register / Vol. 74, No. 129 / Wednesday, July 8, 2009 / Rules and Regulations 

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 5—MATERIAL INCORPORATED BY REFERENCE

Canadair temporary 

revision— Dated— To the— 

5–138 .................................. June 26, 2007 .................... Canadair Challenger Time Limits/Maintenance Checks, PSP 605, Chapter 5, Section 5–10–30. 

5–226 .................................. June 26, 2007 .................... Canadair Challenger Time Limits/Maintenance Checks, PSP 601–5, Chapter 5, Section 5–10–30. 

5–239 .................................. June 26, 2007 .................... Canadair Challenger Time Limits/Maintenance Checks, PSP 601A–5, Chapter 5, 

Section 5–10–30. 

5–2–32 ................................ May 31, 2007 ..................... Canadair Challenger CL–604 Time Limits/Maintenance Checks, Chapter 5, Section 

5–10–40. 

600/23 ................................. January 30, 2007 ............... Canadair Challenger CL–600–1A11 Airplane Flight Manual. 

600–1/18 ............................. January 30, 2007 ............... Canadair Challenger CL–600–1A11 Airplane Flight Manual (Winglets). 

601/15 ................................. January 30, 2007 ............... Canadair Challenger CL–600–2A12 Airplane Flight Manual, PSP 601–1B–1. 

601/16 ................................. January 30, 2007 ............... Canadair Challenger CL–600–2A12 Airplane Flight Manual, PSP 601–1A–1. 

601/20 ................................. January 30, 2007 ............... Canadair Challenger CL–600–2A12 Airplane Flight Manual, PSP 601–1B. 

601/27 ................................. January 30, 2007 ............... Canadair Challenger CL–600–2B16 AFM Airplane Flight Manual PSP 601A–1. 

601/28 ................................. January 30, 2007 ............... Canadair Challenger CL–600–2A12 Airplane Flight Manual. 

601/28 ................................. January 30, 2007 ............... Canadair Challenger CL–600–2B16 Airplane Flight Manual, PSP 601A–1–1. 

604/22 ................................. January 30, 2007 ............... Canadair Challenger CL–604 Airplane Flight Manual, PSP 604–1. 

Issued in Renton, WA, on June 11, 2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–15394 Filed 7–7–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0933; Directorate 

Identifier 2007–NM–261–AD; Amendment 

39–15956; AD 2009–14–06] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 777 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 all Boeing Model 777 

airplanes. That AD currently requires, 

for the drive mechanism of the 

horizontal stabilizer, repetitive detailed 

inspections for discrepancies, repetitive 

lubrication of the ballnut and ballscrew, 

repetitive measurements of the freeplay 

between the ballnut and the ballscrew, 

and corrective action if necessary. This 

new AD revises the compliance times of 

the existing AD. This AD results from a 

report of extensive corrosion of a 

ballscrew in the drive mechanism of the 

horizontal stabilizer on a Boeing Model 

757 airplane, which is similar in design 

to the ballscrew on Model 777 airplanes. 

We are issuing this AD to prevent an 

undetected failure of the primary load 

path for the ballscrew in the drive 

mechanism of the horizontal stabilizer 

and subsequent wear and failure of the 

secondary load path, which could lead 

to loss of control of the horizontal 

stabilizer and consequent loss of control 

of the airplane. 

DATES: This AD becomes effective 

August 12, 2009. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of August 12, 2009. 

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 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: 

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: 

Discussion 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that 

supersedes AD 2007–17–12, amendment 

39–15170 (72 FR 49158, August 28, 

2007). The existing AD applies to all 

Boeing Model 777 airplanes. That 

NPRM was published in the Federal 

Register on August 29, 2008 (73 FR 

50896). That NPRM proposed to retain 

the actions specified in the existing AD 

(i.e., for the drive mechanism of the 

horizontal stabilizer, repetitive detailed 

inspections for discrepancies, repetitive 

lubrication of the ballnut and ballscrew, 

repetitive measurements of the freeplay 

between the ballnut and the ballscrew, 

and corrective action if necessary) but 

with new initial inspection compliance 

times. 

New Service Information 

Since issuance of the NPRM, we have 

reviewed Boeing Service Bulletin 777– 

27A0059, Revision 2, dated January 15, 

2009. This revision of the service 

bulletin is essentially the same as 

Revision 1 of the service bulletin. (We 

referred to Boeing Alert Service Bulletin 

777–27A0059, Revision 1, August 18, 

2005, as the appropriate source of 

service information for doing the actions 

proposed in the NPRM.) Revision 2 of 

the service bulletin specifies similar 


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Federal Register / Vol. 74, No. 129 / Wednesday, July 8, 2009 / Rules and Regulations 32415 

compliance times as those proposed in 

the NPRM, adds clarifying language 

regarding tooling, refers to the 

superseded AD, and defines the phrase 

‘‘known serviceable condition’’ for a 

horizontal stabilizer trim actuator 

(HSTA), including defining the term 

‘‘overhaul.’’ 

Explanation of Removed Service 

Bulletin Reference Paragraph and 

Note 1 

We have removed the ‘‘Service 

Bulletin Reference’’ paragraph (i.e., 

paragraph (f) of the NPRM) and Note 1 

from this AD and included references to 

Boeing Service Bulletin 777–27A0059, 

Revision 2, dated January 15, 2009, in 

paragraphs (g), (h), (i), and (l) of this AD. 

We have added Boeing Alert Service 

Bulletin 777–27A0059, Revision 1, 

dated August 18, 2005, to paragraph (j) 

of this AD to give credit for actions done 

before the effective date of this AD in 

accordance with Revision 1 of the 

service bulletin. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comments that have 

been received on the NPRM. 

Requests for Clarification of 

‘‘Overhaul’’ and ‘‘Serviceable’’ 

The Air Transport Association, on 

behalf of one of its members, American 

Airlines, requests that we clarify the 

meaning of ‘‘overhaul’’ and 

‘‘serviceable’’ in both the NPRM and 

Boeing Alert Service Bulletin 777– 

27A0059, Revision 1, August 18, 2005. 

American Airlines states that the 

NPRM specifies to replace an HSTA 

with a new or ‘‘serviceable’’ unit in 

accordance with Boeing Alert Service 

Bulletin 777–27A0059, Revision 1, 

dated August 18, 2005, and that the 

NPRM also states that no person shall 

install, on any airplane, an HSTA that 

is not new or ‘‘overhauled,’’ unless a 

detailed inspection, freeplay 

measurement, and lubrication of that 

actuator have been performed in 

accordance with paragraphs (h), (i), and 

(j) of the proposed AD (i.e., paragraphs 

(g), (h), and (i) of this final rule). In 

addition, American Airlines states that 

the component maintenance manual 

(CMM) for the subject HSTA does not 

have a defined ‘‘overhaul’’ work scope. 

American Airlines believes that the 

NPRM and the service bulletin should 

provide the specific procedures and/or 

CMM requirements for what constitutes 

an ‘‘overhauled’’ and/or ‘‘serviceable’’ 

HSTA. 

We agree with the commenters. Note 

6 of paragraph 3.A. of Boeing Service 

Bulletin 777–27A0059, Revision 2, 

dated January 15, 2009, now defines the 

phrase ‘‘known serviceable condition’’ 

for an HSTA, including defining the 

term ‘‘overhaul.’’ We have added the 

phrase ‘‘known serviceable condition’’ 

to paragraphs (f)(2) through (f)(4), (g), 

and (h) of this AD in place of the words 

‘‘serviceable HSTA’’ and ‘‘new or 

overhauled’’ in the NPRM to be in line 

with the usage in that service bulletin. 

We have also changed paragraph (l) of 

this AD to refer to the definition of 

‘‘known serviceable condition’’ in that 

service bulletin. In addition, new Note 

1 referring to ‘‘known serviceable 

condition’’ has been added to the final 

rule. 

Conclusion 

We have carefully reviewed the 

available data, including the comments 

that have been received, and determined 

that air safety and the public interest 

require adopting the AD with the 

changes described previously. We have 

determined that these changes will 

neither increase the economic burden 

on any operator nor increase the scope 

of the AD. 

Costs of Compliance 

There are about 596 airplanes of the 

affected design in the worldwide fleet. 

This AD affects about 203 airplanes of 

U.S. registry. The new requirements of 

this AD add no additional economic 

burden. The current costs of the existing 

AD are repeated for the convenience of 

affected operators, as follows. 

The maintenance records check takes 

about 1 work hour per airplane, at an 

average labor rate of $80 per work hour. 

Based on these figures, the estimated 

cost of the maintenance records check 

for U.S. operators is $16,240, or $80 per 

airplane. 

The detailed inspection takes about 1 

work hour per airplane, at an average 

labor rate of $80 per work hour. Based 

on these figures, the estimated cost of 

the inspection for U.S. operators is 

$16,240, or $80 per airplane, per 

inspection cycle. 

The freeplay measurement takes about 

5 work hours per airplane, at an average 

labor rate of $80 per work hour. Based 

on these figures, the estimated cost of 

the freeplay measurement for U.S. 

operators is $81,200, or $400 per 

airplane, per measurement cycle. 

The required lubrication takes about 1 

work hour per airplane, at an average 

labor rate of $80 per work hour. Based 

on these figures, the estimated cost of 

the lubrication for U.S. operators is 

$16,240, or $80 per airplane, per 

lubrication 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 

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. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

(2) Is not a ‘‘significant rule’’ under 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); and 

(3) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

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. 

Adoption of the Amendment 

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 


sroberts on DSKD5P82C1PROD with RULES
32416 Federal Register / Vol. 74, No. 129 / Wednesday, July 8, 2009 / Rules and Regulations 

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 Federal Aviation 

Administration (FAA) amends § 39.13 

by removing amendment 39–15170 (72 

FR 49158, August 28, 2007) and by 

adding the following new airworthiness 

directive (AD): 

2009–14–06 Boeing: Amendment 39–15956. 

Docket No. FAA–2008–0933; Directorate 

Identifier 2007–NM–261–AD. 

Effective Date 

(a) This AD becomes effective August 12, 

2009. 

Affected ADs 

(b) This AD supersedes AD 2007–17–12. 

Applicability 

(c) This AD applies to all Boeing Model 

777 airplanes, certificated in any category. 

Unsafe Condition 

(d) This AD results from a report of 

extensive corrosion of a ballscrew in the 

drive mechanism of the horizontal stabilizer 

on a Boeing Model 757 airplane, which is 

similar in design to the ballscrew on Model 

777 airplanes. We are issuing this AD to 

prevent an undetected failure of the primary 

load path for the ballscrew in the drive 

mechanism of the horizontal stabilizer and 

subsequent wear and failure of the secondary 

load path, which could lead to loss of control 

of the horizontal stabilizer 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. 

Restatement of Requirements of AD 2007– 

17–12 With Revised Compliance Times and 

Updated Service Information 

Maintenance Records Check 

(f) For airplanes that have received an 

original airworthiness certificate or original 

export certificate of airworthiness prior to the 

effective date of this AD: Within 180 days or 

3,500 flight hours after the effective date of 

this AD, whichever occurs first, perform a 

maintenance records check or inspect to 

determine the status of the horizontal 

stabilizer trim actuator (HSTA) as specified 

in paragraph (f)(1), (f)(2), (f)(3), or (f)(4) of 

this AD, as applicable: 

(1) The original HSTA delivered with the 

airplane has not been removed and is still 

installed on the airplane; 

(2) The original HSTA has been replaced 

with an HSTA in a known serviceable 

condition; 

(3) The original HSTA has been replaced 

with an HSTA that is not in a known 

serviceable condition, and which has not 

received a detailed inspection and freeplay 

measurement as described in paragraphs (g) 

and (h) of this AD since that replacement; or 

(4) The original HSTA has been replaced 

with an HSTA that is not in a known 

serviceable condition, and which has 

received a detailed inspection and freeplay 

measurement as described in paragraphs (g) 

and (h) of this AD since that replacement. 

Note 1: The phrase ‘‘known serviceable 

condition’’ is defined in section 3.A., Note 6, 

of Boeing Service Bulletin 777–27A0059, 

Revision 2, dated January 15, 2009. 

Detailed Inspection 

(g) Within the compliance times specified 

in paragraphs (g)(1), (g)(2), (g)(3), and (g)(4) 

of this AD, as applicable: Perform a detailed 

inspection for discrepancies of the horizontal 

stabilizer trim actuator ballnut and ballscrew, 

in accordance with Part 1 of the 

Accomplishment Instructions of Boeing 

Service Bulletin 777–27A0059, Revision 2, 

dated January 15, 2009. Repeat the detailed 

inspection thereafter at intervals not to 

exceed 3,500 flight hours or 12 months, 

whichever occurs first. If any discrepancy is 

found during any inspection required by this 

AD, before further flight, replace the actuator 

with an actuator in a known serviceable 

condition, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 777–27A0059, Revision 2, 

dated January 15, 2009. 

(1) For airplanes identified in paragraph 

(f)(1) of this AD: Before the accumulation of 

15,000 total flight hours, or within 18 months 

after the effective date of this AD, whichever 

occurs later. 

(2) For airplanes identified in paragraph 

(f)(2) or (f)(4) of this AD: Before the 

accumulation of 15,000 flight hours since the 

replacement of the HSTA, or within 18 

months after the effective date of this AD, 

whichever occurs later. 

(3) For airplanes identified in paragraph 

(f)(3) of this AD: Before the accumulation of 

3,500 flight hours since the replacement of 

the HSTA, or within 12 months after the 

effective date of this AD, whichever occurs 

later. 

(4) For airplanes that have received an 

original airworthiness certificate or original 

export certificate of airworthiness on or after 

the effective date of this AD: Before the 

accumulation of 15,000 total flight hours, or 

within 18 months after the issuance of the 

original airworthiness certificate or original 

export certificate of airworthiness, whichever 

occurs later. 

Freeplay Measurement (Inspection) 

(h) Within the compliance times specified 

in paragraphs (h)(1), (h)(2), (h)(3), and (h)(4) 

of this AD, as applicable: Perform a freeplay 

measurement of the ballnut and ballscrew in 

accordance with Part 2 of the 

Accomplishment Instructions of Boeing 

Service Bulletin 777–27A0059, Revision 2, 

dated January 15, 2009. Repeat the freeplay 

measurement thereafter at intervals not to 

exceed 18,000 flight hours or 60 months, 

whichever occurs first. If the freeplay is 

found to exceed the limits specified in the 

service bulletin during any measurement 

required by this AD, before further flight, 

replace the actuator with an actuator in a 

known serviceable condition, in accordance 

with the Accomplishment Instructions of 

Boeing Service Bulletin 777–27A0059, 

Revision 2, dated January 15, 2009. 

(1) For airplanes identified in paragraph 

(f)(1) of this AD: Before the accumulation of 

15,000 total flight hours, or within 18 months 

after the effective date of this AD, whichever 

occurs later. 

(2) For airplanes identified in paragraph 

(f)(2) or (f)(4) of this AD: Before the 

accumulation of 15,000 flight hours since the 

replacement of the HSTA, or within 18 

months after the effective date of this AD, 

whichever occurs later. 

(3) For airplanes identified in paragraph 

(f)(3) of this AD: Before the accumulation of 

3,500 flight hours since the replacement of 

the HSTA, or within 12 months after the 

effective date of this AD, whichever occurs 

later. 

(4) For airplanes that have received an 

original airworthiness certificate or original 

export certificate of airworthiness on or after 

the effective date of this AD: Before the 

accumulation of 15,000 total flight hours, or 

within 18 months after the issuance of the 

original airworthiness certificate or original 

export certificate of airworthiness, whichever 

occurs later. 

Lubrication 

(i) Within the compliance times specified 

in paragraphs (i)(1), (i)(2), (i)(3), and (i)(4) of 

this AD, as applicable: Lubricate the ballnut 

and ballscrew in accordance with Part 3 of 

the Accomplishment Instructions of Boeing 

Service Bulletin 777–27A0059, Revision 2, 

dated January 15, 2009. Repeat the 

lubrication thereafter at intervals not to 

exceed 2,000 flight hours or 12 months, 

whichever occurs first. 

(1) For airplanes identified in paragraph 

(f)(1) of this AD: Before the accumulation of 

15,000 total flight hours, or within 18 months 

after the effective date of this AD, whichever 

occurs later. 

(2) For airplanes identified in paragraph 

(f)(2) or (f)(4) of this AD: Before the 

accumulation of 15,000 flight hours since the 

replacement of the HSTA, or within 18 

months after the effective date of this AD, 

whichever occurs later. 

(3) For airplanes identified in paragraph 

(f)(3) of this AD: Before the accumulation of 

3,500 flight hours since the replacement of 

the HSTA, or within 12 months after the 

effective date of this AD, whichever occurs 

later. 

(4) For airplanes that have received an 

original airworthiness certificate or original 

export certificate of airworthiness on or after 

the effective date of this AD: Before the 

accumulation of 15,000 total flight hours, or 

within 18 months after the issuance of the 

original airworthiness certificate or original 

export certificate of airworthiness, whichever 

occurs later. 

Credit for Actions Accomplished According 

to Earlier Issues of the Service Bulletin 

(j) Actions performed prior to the effective 

date of this AD, in accordance with Boeing 

Alert Service Bulletin 777–27A0059, dated 

September 18, 2003; or Boeing Alert Service 


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Federal Register / Vol. 74, No. 129 / Wednesday, July 8, 2009 / Rules and Regulations 32417 

Bulletin 777–27A0059, Revision 1, dated 

August 18, 2005; are considered acceptable 

for compliance with the corresponding 

actions specified in paragraphs (g), (h), and 

(i) of this AD. 

Credit for Hard-Time Replacement of HSTA 

(k) Any HSTA overhauled within the 

compliance times specified in paragraphs (g), 

(h), and (i) of this AD or before the effective 

date of this AD—as part of a ‘‘hard-time’’ 

replacement program that includes removal 

of the HSTA from the airplane and overhaul 

of the stabilizer ballscrew in accordance with 

original equipment manufacturer component 

maintenance manual instructions—meets the 

intent of one detailed inspection, one 

freeplay inspection, and one lubrication of 

the HSTA. Therefore, any such HSTA is 

considered acceptable for compliance with 

the initial accomplishment of the actions 

specified in paragraphs (g), (h), and (i) of this 

AD, and repetitions of those actions may be 

determined from the performance date of that 

overhaul. 

Parts Installation 

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

person may install, on any airplane, a 

horizontal stabilizer trim actuator that is not 

in a ‘‘known serviceable condition’’ as 

defined in Note 6, section 3.A., of Boeing 

Alert Service Bulletin 777–27A0059, 

Revision 2, dated January 15, 2009; unless a 

detailed inspection, freeplay measurement, 

and lubrication of that actuator are performed 

in accordance with paragraphs (g), (h), and (i) 

of this AD, as applicable. 

Alternative Methods of Compliance 

(AMOCs) 

(m)(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, 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; has the 

authority to approve AMOCs for this AD, if 

requested using 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. 

Material Incorporated by Reference 

(n) You must use Boeing Service Bulletin 

777–27A0059, Revision 2, dated January 15, 

2009, 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 or 425–227–1152. 

(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, WA, on June 24, 2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–15639 Filed 7–7–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0380; Directorate 

Identifier 2008–NM–153–AD; Amendment 

39–15959; AD 2009–14–09] 

RIN 2120–AA64 

Airworthiness Directives; Dassault 

Model Falcon 2000EX 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: 

An internal review of design data has 

shown that the web of the left hand side (LH) 

stringer 13 near frame 8 might have been 

improperly trimmed on a few aircraft. 

If not corrected, possible crack initiations 

could occur in the upper stringer web, and 

therefore could impair the structural strength 

of the adjacent door stop. This latent failure 

could ultimately lead to the loss of 

redundancy of the door stops, thereby 

affecting the structural integrity of the 

fuselage. 

* * * * * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

August 12, 2009. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of August 12, 2009. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: Tom 

Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

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 April 27, 2009 (74 FR 

19027). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

An internal review of design data has 

shown that the web of the left hand side (LH) 

stringer 13 near frame 8 might have been 

improperly trimmed on a few aircraft. 

If not corrected, possible crack initiations 

could occur in the upper stringer web, and 

therefore could impair the structural strength 

of the adjacent door stop. This latent failure 

could ultimately lead to the loss of 

redundancy of the door stops, thereby 

affecting the structural integrity of the 

fuselage. 

Computational analysis has revealed a 

substantial reduced fatigue life for the 

stringer abutting onto the improperly 

trimmed web and has determined the need 

for an inspection and repair action no later 

than the first ‘‘C’’ check. 

To address this unsafe condition, the 

present Airworthiness Directive (AD) 

mandates an inspection and a conditional 

rework or replacement of the web of the LH 

stringer 13 between frames 7 and 8. 

Required actions include measuring the 

trimmed length of the web, inspecting 

for any sharp and unprotected edges of 

the web, and doing corrective actions if 

necessary. Corrective actions include 

reworking the web and applying 

protection to the web, or replacing the 

web, if improperly trimmed. 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 


sroberts on DSKD5P82C1PROD with RULES