Federal Register / Vol. 75, No. 51 / Wednesday, March 17, 2010 / Rules and Regulations 12667 

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. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

■ Accordingly, pursuant to the authority 

delegated to me by the Administrator, 

the Federal Aviation Administration 

amends part 39 of the Federal Aviation 

Regulations (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. Section 39.13 is amended by adding 

a new airworthiness directive to read as 

follows: 

2010–06–08 Sikorsky Aircraft Corporation: 

Amendment 39–16232. Docket No. 

FAA–2010–0242; Directorate Identifier 

2009–SW–27–AD. 

Applicability: Sikorsky Aircraft 

Corporation Model S–76C helicopters, serial 

numbers 760501 and 760506 through 760761, 

with Option Code 88051 Flotation System 

installed by Keystone Helicopter 

Corporation, certificated in any category. 

Compliance: Before the next flight over 

water, or within 30 days, whichever occurs 

first, unless accomplished previously. 

To determine if a metallic foil shunt is 

installed in the flotation system, which could 

prevent the flotation system from deploying 

and could prevent the helicopter from 

staying afloat long enough to enable 

emergency evacuation after a water landing, 

accomplish the following: 

(a) Inspect the flotation system connector 

and if a metallic foil shunt is found, remove 

it in accordance with the Accomplishment 

Instructions, paragraphs 3.A.(1) through 

3.A.(9), in Sikorsky Alert Service Bulletin 

No. 76–32–30, dated April 8, 2009. 

(b) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Contact the Manager, Boston Aircraft 

Certification Office, FAA, Attn: Terry Fahr, 

12 New England Executive Park, Burlington, 

MA 01803, telephone (781) 238–7155, fax 

(781) 238–7170. 

(c) The inspection shall be done in 

accordance with the specified portions of 

Sikorsky Alert Service Bulletin No. 76–32– 

30, dated April 8, 2009. The Director of the 

Federal Register approved this incorporation 

by reference in accordance with 5 U.S.C. 

552(a) and 1 CFR part 51. Copies may be 

obtained from Sikorsky Aircraft Corporation, 

Attn: Manager, Commercial Technical 

Support, mailstop s581a, 6900 Main Street, 

Stratford, CT, telephone (203) 383–4866, email address tsslibrary@sikorsky.com, or at 

http://www.sikorsky.com. Copies may be 

inspected at the FAA, Office of the Regional 

Counsel, Southwest Region, 2601 Meacham 

Blvd., Room 663, Fort Worth, Texas 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. 

Joint Aircraft System/Component (JASC) 

Code 

(d) JASC Code 3212: Emergency Flotation 

Systems. 

(e) This amendment becomes effective on 

April 1, 2010. 

Issued in Fort Worth, Texas, on February 

3, 2010. 

Mark R. Schilling, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–5294 Filed 3–16–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0226; Directorate 

Identifier 2010–NM–034–AD; Amendment 

39–16238; AD 2010–06–13] 

RIN 2120–AA64 

Airworthiness Directives; Learjet Inc. 

Model 45 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Model 45 airplanes. This AD requires a 

general visual inspection for cracked 

and missing ballscrew assembly sleeves 

of the flap actuator, repetitive nondestructive liquid penetrant inspections 

of each sleeve or flap actuator for cracks, 

and replacement or modification of the 

flap actuator if necessary. This AD 

results from reports of cracked and 

missing ballscrew assembly sleeves of 

the flap actuators. We are issuing this 

AD to detect and correct cracked and 

missing sleeves, which could cause loss 

of the load-carrying ball bearings on 

both actuators on one flap, resulting in 

flap asymmetry and loss of control of 

the airplane. 

DATES: This AD is effective April 1, 

2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of April 1, 2010. 

We must receive comments on this 

AD by May 3, 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 Learjet, Inc., One 

Learjet Way, Wichita, Kansas 67209– 

2942; telephone 316–946–2000; fax 

316–946–2220; e-mail 

ac.ict@aero.bombardier.com; Internet 

http://www.bombardier.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: 

William Griffith, Aerospace Engineer, 

Airframe Branch, ACE–118W, FAA, 

Wichita Aircraft Certification Office, 

1801 Airport Road, Room 100, MidVerDate Nov<24>2008 14:47 Mar 16, 2010 Jkt 220001 PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 E:\FR\FM\17MRR1.SGM 17MRR1

wwoods2 on DSK1DXX6B1PROD with RULES_PART 1
12668 Federal Register / Vol. 75, No. 51 / Wednesday, March 17, 2010 / Rules and Regulations 

Continent Airport, Wichita, Kansas 

67209; telephone (316) 946–4116; fax 

(316) 946–4107. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We have received reports of cracked 

and missing ballscrew assembly sleeves 

of the flap actuators. Three flap 

actuators were found with the ballnut 

sleeves corroded and cracked. Three 

additional airplanes were discovered to 

contain similar corrosion on the ballnut 

sleeves. The root cause is galvanic 

corrosion due to an aluminum sleeve 

installed on a steel ballnut. This 

condition, if not corrected, could cause 

loss of the load-carrying ball bearings on 

both actuators on one flap, resulting in 

flap asymmetry and loss of control of 

the airplane. 

Relevant Service Information 

We reviewed Bombardier (Learjet) 

Alert Service Bulletins A45–27–40 (for 

Model 45 airplanes, serial numbers 45– 

005 through 45–380), and A40–27–24 

(for Model 45 airplanes, serial numbers 

45–2001 through 45–2111), both dated 

January 11, 2010. These service 

bulletins describe procedures for a 

general visual inspection for cracked 

and missing ballscrew assembly sleeves 

of the flap actuator; a non-destructive 

liquid penetrant inspection for cracks of 

each sleeve and flap actuator, 

depending on the findings; and 

replacement of the flap actuator and 

ballscrew actuator sleeve if the sleeve is 

cracked along its entire length. 

We also reviewed Bombardier 

(Learjet) Optional Service Bulletins 45– 

27–41 (for Model 45 airplanes, serial 

numbers 45–005 through 45–380), and 

40–27–25 (for Model 45 airplanes, serial 

numbers 45–2001 through 45–2111), 

both dated January 11, 2010. These 

service bulletins describe procedures for 

modifying the flap actuator if a certain 

crack length is found and the part does 

not need to be replaced. 

FAA’s Determination and Requirements 

of This AD 

We are issuing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. This AD requires 

accomplishing the actions specified in 

the service information described 

previously, except as discussed under 

‘‘Differences Between the AD and the 

Service Information.’’ 

Differences Between the AD and the 

Service Information 

Although Bombardier (Learjet) Alert 

Service Bulletins A45–27–40 and A40– 

27–24, both dated January 11, 2010, 

specify a compliance time of 30 days 

after the publication of those service 

bulletins, this AD requires a compliance 

time of 15 days after the effective date 

of this AD. We have received additional 

reports of fully cracked sleeves 

requiring replacement. Therefore, we 

have determined that the 15-day 

compliance time is necessary to address 

the identified unsafe condition. This 

difference has been coordinated with 

Learjet. 

Although Bombardier (Learjet) Alert 

Service Bulletins A45–27–40 and A40– 

27–24, both dated January 11, 2010, do 

not specify repetitive inspections, this 

AD requires operators to repeat the nondestructive liquid penetrant inspections 

at intervals not to exceed 6 months. The 

repetitive inspections will help 

determine the extent of the problem in 

the fleet. This difference has been 

coordinated with Learjet. 

Although Bombardier (Learjet) Alert 

Service Bulletins A45–27–40 and A40– 

27–24, both dated January 11, 2010, 

specify to inspect for missing ballscrew 

assembly sleeves, these service bulletins 

do not specify a corrective action if any 

sleeve is missing. This AD requires 

replacing the flap actuator if any sleeve 

is missing. This difference has been 

coordinated with Learjet. 

Bombardier (Learjet) Alert Service 

Bulletins A45–27–40 and A40–27–24, 

both dated January 11, 2010, specify 

modifying or replacing the flap actuator 

as corrective action for a cracked sleeve, 

depending on the percentage of the 

length of the sleeve that is cracked. This 

AD instead requires replacing the 

actuator if a sleeve is cracked along its 

entire length, and modifying the 

actuator for any cracked sleeve that is 

not cracked along its entire length. This 

difference has been coordinated with 

Learjet. 

Interim Action 

We consider this AD interim action. 

Learjet Inc. is currently developing a 

new modification of the ballscrew 

assembly of the flap actuator that will 

address the unsafe condition identified 

in this AD. Once this modification is 

developed, approved, and available, we 

might consider additional rulemaking. 

FAA’s Justification and Determination 

of the Effective Date 

We have received reports of cracked 

and missing ballscrew assembly sleeves 

of the flap actuators. Cracked and 

missing sleeves could result in the loss 

of the load-carrying ball bearings from 

the assembly, resulting in the loss of the 

flap drive load path for that actuator. 

Loss of the sleeves on both actuators on 

one flap could result in flap asymmetry, 

resulting in loss of control of the 

airplane. Because of our requirement to 

promote safe flight of civil aircraft and 

thus the critical need to ensure 

structural integrity of the ballscrew 

assembly sleeves of the flap actuator 

and the short compliance time involved 

with this action, this AD must be issued 

immediately. 

Because an unsafe condition exists 

that requires the immediate adoption of 

this AD, we find that notice and 

opportunity for prior public comment 

hereon are impracticable and that good 

cause exists for making this amendment 

effective in less than 30 days. 

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– 

2010–0226; Directorate Identifier 2010– 

NM–034–AD’’ at the beginning of your 

comments. We specifically invite 

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 


wwoods2 on DSK1DXX6B1PROD with RULES_PART 1
Federal Register / Vol. 75, No. 51 / Wednesday, March 17, 2010 / Rules and Regulations 12669 

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: 

2010–06–13 Learjet Inc.: Amendment 39– 

16238. Docket No. FAA–2010–0226; 

Directorate Identifier 2010–NM–034–AD. 

Effective Date 

(a) This airworthiness directive (AD) is 

effective April 1, 2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Learjet Inc. Model 

45 airplanes, certificated in any category, 

serial numbers 45–005 through 45–380 

inclusive and 45–2001 through 45–2111 

inclusive. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 27: Flight Controls. 

Unsafe Condition 

(e) This AD results from reports of cracked 

and missing ballscrew assembly sleeves of 

the flap actuators. The Federal Aviation 

Administration is issuing this AD to detect 

and correct cracked and missing sleeves, 

which could cause loss of the load-carrying 

ball bearings on both actuators on one flap, 

resulting in flap asymmetry and loss of 

control of the airplane. 

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. 

General Visual Inspection 

(g) Within 15 days after the effective date 

of this AD, do a general visual inspection for 

cracked or missing ballscrew assembly 

sleeves of the flap actuator, in accordance 

with the Accomplishment Instructions of 

Bombardier (Learjet) Alert Service Bulletin 

A45–27–40 (for Model 45 airplanes, serial 

numbers 45–005 through 45–380); or 

Bombardier (Learjet) Alert Service Bulletin 

A40–27–24 (for Model 45 airplanes, serial 

numbers 45–2001 through 45–2111); both 

dated January 11, 2010. Thereafter, do the 

actions in paragraph (h) or (i), as applicable, 

of this AD. 

Note 1: For the purposes of this AD, a 

general visual inspection is: ‘‘A visual 

examination of an interior or exterior area, 

installation, or assembly to detect obvious 

damage, failure, or irregularity. This level of 

inspection is made from within touching 

distance unless otherwise specified. A mirror 

may be necessary to ensure visual access to 

all surfaces in the inspection area. This level 

of inspection is made under normally 

available lighting conditions such as 

daylight, hangar lighting, flashlight, or 

droplight and may require removal or 

opening of access panels or doors. Stands, 

ladders, or platforms may be required to gain 

proximity to the area being checked.’’ 

Non-Destructive Liquid Penetrant Inspection 

(Sleeve Is Present and Not Cracked Along Its 

Entire Length) 

(h) During the general visual inspection 

required by paragraph (g) of this AD, if the 

sleeve is present and not cracked along its 

entire length, before further flight after 

accomplishing the general visual inspection, 

do a non-destructive liquid penetrant 

inspection to detect cracking of the flap 

actuators, in accordance with 

Accomplishment Instructions of Bombardier 

(Learjet) Alert Service Bulletin A45–27–40, 

or Bombardier (Learjet) Alert Service Bulletin 

A40–27–24, both dated January 11, 2010. 

(1) If no crack is found during the nondestructive liquid penetrant inspection, 

repeat the inspection thereafter at intervals 

not to exceed 6 months. 

(2) If any crack is found during the nondestructive liquid penetrant inspection, 

before further flight, modify the flap actuator, 

in accordance with the Accomplishment 

Instructions of Bombardier (Learjet) Optional 

Service Bulletin 45–27–41 (for Model 45 

airplanes, serial numbers 45–005 through 

45–380); or Bombardier (Learjet) Optional 

Service Bulletin 40–27–25 (for Model 45 

airplanes, serial numbers 45–2001 through 

45–2111); both dated January 11, 2010. 

Repeat the non-destructive liquid penetrant 

inspection of the half (modified) sleeve 

thereafter at intervals not to exceed 6 months. 

If any crack is found in any half (modified) 

sleeve, before further flight, replace the 

sleeve with a new half sleeve, in accordance 

with the Accomplishment Instructions of 

Bombardier (Learjet) Optional Service 

Bulletin 45–27–41, or Bombardier (Learjet) 

Optional Service Bulletin 40–27–25, both 

dated January 11, 2010, and repeat the nondestructive liquid penetrant inspection of the 

half sleeve thereafter at intervals not to 

exceed 6 months. 

Replacement (Sleeve Is Missing or Cracked 

Along Its Entire Length) 

(i) During the general visual inspection 

required by paragraph (g) of this AD, if the 

sleeve is missing or cracked along its entire 

length, before further flight after 

accomplishing the general visual inspection, 

replace the actuator with a new or 

serviceable actuator, in accordance with the 

Accomplishment Instructions of Bombardier 

(Learjet) Alert Service Bulletin A45–27–40, 

or Bombardier (Learjet) Alert Service Bulletin 

A40–27–24, both dated January 11, 2010. 

Within 6 months after any actuator 

replacement required by paragraph (i) of this 

AD: Do a non-destructive liquid penetrant 

inspection to detect cracking of the actuator, 

in accordance with Accomplishment 

Instructions of Bombardier (Learjet) Alert 

Service Bulletin A45–27–40, or Bombardier 

(Learjet) Alert Service Bulletin A40–27–24, 

both dated January 11, 2010. 

(1) If no crack is found during the nondestructive liquid penetrant inspection, 

repeat the inspection thereafter at intervals 

not to exceed 6 months. 

(2) If any crack is found during the nondestructive liquid penetrant inspection, but 

the sleeve is not cracked along its entire 

length, before further flight, modify the flap 

actuator, in accordance with the 

Accomplishment Instructions of Bombardier 

(Learjet) Optional Service Bulletin 45–27–41, 

or Bombardier (Learjet) Optional Service 

Bulletin 40–27–25, both dated January 11, 

2010. Repeat the non-destructive liquid 

penetrant inspection of the half (modified) 

sleeves thereafter at intervals not to exceed 

6 months. If any crack is found in any half 

(modified) sleeve, before further flight, 

replace the sleeve with a new half sleeve, in 

accordance with the Accomplishment 

Instructions of Bombardier (Learjet) Optional 

Service Bulletin 45–27–41, or Bombardier 

(Learjet) Optional Service Bulletin 40–27–25, 

both dated January 11, 2010. Repeat the nondestructive liquid penetrant inspection of the 

half sleeve thereafter at intervals not to 

exceed 6 months. 

(3) If the sleeve is cracked along its entire 

length, before further flight, replace the 

actuator with a new or serviceable actuator, 

in accordance with the Accomplishment 

Instructions of Bombardier (Learjet) Optional 


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12670 Federal Register / Vol. 75, No. 51 / Wednesday, March 17, 2010 / Rules and Regulations 

Service Bulletin 45–27–41, or Bombardier 

(Learjet) Optional Service Bulletin 40–27–25, 

both dated January 11, 2010, and repeat the 

non-destructive liquid penetrant inspection 

of the sleeve thereafter at intervals not to 

exceed 6 months. 

Note 2: Guidance on modification of the 

flap actuator can be found in Microtecnica 

Service Bulletin 27–0018, dated November 

24, 2009. 

Parts Installation 

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

person may install, on any airplane, a 

ballscrew assembly sleeve of the flap 

actuator, unless the actuator has been 

modified according to Bombardier (Learjet) 

Optional Service Bulletin 45–27–41, or 

Bombardier (Learjet) Optional Service 

Bulletin 40–27–25, both dated January 11, 

2010. 

Reporting Requirement 

(k) Submit a one-time report of the findings 

of the general visual inspection and the 

initial non-destructive liquid penetrant 

inspection required by this AD to Chris 

Broadrick, Bombardier Aerospace, Project 

Coordinator—Fielding Specialist, Customer 

Support Engineering, One Learjet Way, P.O. 

Box 7707, Wichita, Kansas 67209; telephone 

316–946–2315; fax 316–946–8908; e-mail 

chris.broadrick@aero.bombardier.com; at the 

applicable time specified in paragraph (k)(1) 

or (k)(2) of this AD. The report must include 

airplane serial number, flap actuator part 

number, flap actuator serial number, and flap 

actuator time in service (in hours). 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 

within 10 days after the effective date of this 

AD. 

Special Flight Permits 

(l) Special flight permits may be issued in 

accordance with sections 21.197 and 21.199 

of the Federal Aviation Regulations (14 CFR 

21.197 and 21.199) to operate the airplane to 

a location where the airplane can be 

modified, unless cracks are discovered in 

both an inboard and outboard actuator sleeve 

for any flap. 

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: 

William Griffith, Aerospace Engineer, 

Airframe Branch, ACE–118W, FAA, Wichita 

ACO, 1801 Airport Road, Room 100, MidContinent Airport, Wichita, Kansas 67209; 

telephone (316) 946–4116; 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. 

Material Incorporated by Reference 

(n) You must use the service information 

included in Table 1 of this AD, as applicable, 

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 Learjet, Inc., One Learjet 

Way, Wichita, Kansas 67209–2942; telephone 

316–946–2000; fax 316–946–2220; e-mail 

ac.ict@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. 

TABLE 1—MATERIAL INCORPORATED

BY REFERENCE

Document Date 

Bombardier (Learjet) 

Alert Service Bulletin 

A40–27–24.

January 11, 2010. 

Bombardier (Learjet) 

Alert Service Bulletin 

A45–27–40.

January 11, 2010. 

Bombardier (Learjet) 

Optional Service Bulletin 40–27–25.

January 11, 2010. 

Bombardier (Learjet) 

Optional Service Bulletin 45–27–41.

January 11, 2010. 

Issued in Renton, Washington, on March 9, 

2010. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–5669 Filed 3–16–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0642; Directorate 

Identifier 2009–NM–001–AD; Amendment 

39–16241; AD 2010–06–16] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 767 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Model 767 series airplanes. This AD 

requires inspections for scribe lines in 

the fuselage skin at skin lap joints, the 

skin at certain external approved 

repairs, the skin around external 

features such as antennas, and the skin 

at decals; and related investigative and 

corrective actions if necessary. This AD 

results from reports of scribe lines found 

at skin lap joints and butt joints, around 

external repairs and antennas, and at 

locations where external decals had 

been cut. We are issuing this AD to 

detect and correct scribe lines, which 

can develop into fatigue cracks in the 

skin and cause sudden decompression 

of the airplane. 

DATES: This AD is effective April 21, 

2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of April 21, 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. 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 AD, the regulatory 

evaluation, any comments received, and 


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