4482 Federal Register / Vol. 75, No. 18 / Thursday, January 28, 2010 / Rules and Regulations 

DVI–10000–3) and Corrosion Prevention and 

Control Programme Task C53–230–02–01. 

For the reason described above, this AD 

requires repetitive [detailed] inspections of 

the Frame 29 wing-to-fuselage attachment lug 

plate joint [for discrepancies, which are 

corrosion and fatigue cracking of the bolts 

and fastener bores; degraded, cracked, 

missing, and poor condition sealant] and 

repair(s) [which include replacing bolts, 

contacting BAE Systems for repair 

instructions and doing the repair and reapplying sealant], as necessary. 

The unsafe condition is degradation of the 

structural integrity of Frame 29 and the wingto-fuselage attachment, which could result in 

loss of control of the airplane. 

Actions and Compliance 

(f) Unless already done, do the following 

actions. 

(1) Within 24 months after the effective 

date of this AD, do a detailed inspection for 

discrepancies of the frame 29 wing-tofuselage attachment lug plate joint, in 

accordance with the Accomplishment 

Instructions of BAE SYSTEMS (Operations) 

Limited Inspection Service Bulletin ISB.53– 

213, dated May 21, 2008. 

Note 1: For the purposes of this AD, a 

detailed inspection is: ‘‘An intensive 

examination of a specific item, installation, 

or assembly to detect damage, failure, or 

irregularity. Available lighting is normally 

supplemented with a direct source of good 

lighting at an intensity deemed appropriate. 

Inspection aids such as mirror, magnifying 

lenses, etc., may be necessary. Surface 

cleaning and elaborate procedures may be 

required.’’ 

(2) Repeat the inspection required by 

paragraph (f)(1) of this AD thereafter at 

intervals not to exceed 48 months. 

(3) During any inspection required by 

paragraph (f)(1) or (f)(2) of this AD, if it is not 

possible to replace a removed bolt with 

another bolt having the same part number as 

a replacement item, before further flight, 

contact BAE SYSTEMS to replace the 

removed bolt with an alternative bolt and do 

the approved BAE SYSTEMS repair. 

(4) If during any inspection required by 

paragraph (f)(1) or (f)(2) of this AD, any 

discrepancy is found, before further flight, 

repair in accordance with paragraph 2.C. of 

the Accomplishment Instructions of BAE 

SYSTEMS (Operations) Limited Inspection 

Service Bulletin ISB.53–213, dated May 21, 

2008. 

(5) Although BAE SYSTEMS (Operations) 

Limited Inspection Service Bulletin ISB.53– 

213, dated May 21, 2008, specifies to submit 

certain information to the manufacturer, this 

AD does not include that requirement. 

FAA AD Differences 

Note 2: This AD differs from the MCAI 

and/or service information as follows: 

Although BAE SYSTEMS (Operations) 

Limited Inspection Service Bulletin ISB.53– 

213, dated May 21, 2008; and European 

Aviation Safety Agency (EASA) AD 2009– 

0046, dated March 2, 2009; specify to submit 

certain information to the manufacturer, this 

AD does not include that requirement. 

Other FAA AD Provisions 

(g) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, 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: Todd Thompson, 

Aerospace Engineer, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

227–1175; fax (425) 227–1149. 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. 

Related Information 

(h) Refer to MCAI EASA Airworthiness 

Directive 2009–0046, dated March 2, 2009; 

and BAE SYSTEMS (Operations) Limited 

Inspection Service Bulletin ISB.53–213, 

dated May 21, 2008; for related information. 

Material Incorporated by Reference 

(i) You must use BAE SYSTEMS 

(Operations) Limited Inspection Service 

Bulletin ISB.53–213, dated May 21, 2008, 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 BAE Systems Regional 

Aircraft, 13850 McLearen Road, Herndon, 

Virginia 20171; telephone 703–736–1080; email raebusiness@baesystems.com; Internet 

http://www.baesystems.com/Businesses/ 

RegionalAircraft/index.htm. 

(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, Washington, on January 

14, 2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–1283 Filed 1–27–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0047; Directorate 

Identifier 2009–SW–28–AD; Amendment 39– 

16177; AD 2010–02–07] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

France Model SE3160, SA315B, 

SA316B, SA316C, and SA319B 

Helicopters 

AGENCY: Federal Aviation 

Administration, DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: This amendment supersedes 

an existing airworthiness directive (AD) 

for the specified Eurocopter France 

(Eurocopter) model helicopters. The 

existing AD requires certain inspections 

of a main rotor blade (blade) 

manufactured under a Parts 

Manufacturer Approval under 

Supplemental Type Certificate (STC) 

SH778GL. The AD requires inspecting 

each affected root end bolt (bolt) and 

bolt-hole for corrosion or a crack on the 

blade root end fitting (fitting) or in a 

bolt-hole. For certain serial-numbered 

blades, the AD also requires a one-time 

pull test on each fitting and blade root 

end doubler (doubler) to detect 

disbonding. This AD requires certain 

inspections for voids in any doubler or 

fitting and for paint cracks along the 

forward and aft edge of the blade fitting. 

Also, this AD requires inspecting the 

blade tip weight housing attachment. 

This AD also requires replacing 

unairworthy blades with airworthy 

blades. This amendment is prompted by 

reports from the STC holder of disbonds 

at the fittings, doublers, and the tip 

weight fitting. The actions specified by 

this AD are intended to prevent blade 

failure and subsequent loss of control of 

the helicopter. 

DATES: Effective February 12, 2010. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of February 

12, 2010. 


rmajette on DSK29S0YB1PROD with RULES
Federal Register / Vol. 75, No. 18 / Thursday, January 28, 2010 / Rules and Regulations 4483 

Comments for inclusion in the Rules 

Docket must be received on or before 

March 29, 2010. 

ADDRESSES: Use one of the following 

addresses to submit comments on this 

AD: 

• 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. 

You may get the service information 

identified in this AD from Phlight of 

Phancy Corp. (PPC), 791 Westport 

Parkway, Fort Worth, Texas 76177– 

4511, telephone 817–491–6755, fax 

817–491–6759. 

Examining the Docket: You may 

examine the docket that contains the 

AD, any comments, and other 

information on the Internet at http:// 

www.regulations.gov, or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The Docket 

Operations office (telephone (800) 647– 

5527) is located in Room W12–140 on 

the ground floor of the West Building at 

the street address stated in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

DOT/FAA Southwest Region, Martin R. 

Crane, ASW–170, Aviation Safety 

Engineer, Rotorcraft Directorate, 

Rotorcraft Certification Office, 2601 

Meacham Blvd., Fort Worth, Texas 

76137, telephone (817) 222–5170, fax 

(817) 222–5783. 

SUPPLEMENTARY INFORMATION: On July 

16, 2003, the FAA issued an Emergency 

AD 2003–15–51. That Emergency AD 

was published as a final rule on August 

28, 2003 (68 FR 51681). The current AD 

requires certain inspections of a blade 

manufactured under a PMA issued and 

based on STC SH778GL. The AD 

requires inspecting each bolt and bolthole for corrosion or a crack on the 

fitting or in a bolt-hole on each affected 

blade. For certain serial-numbered 

blades, the AD also requires a one-time 

pull test on each fitting and doubler to 

detect disbonding. That action was 

prompted by a report from the blade 

manufacturer of the discovery of a 

cracked blade. In that action, we stated 

that the cause of the crack remained 

under investigation. That condition, if 

not corrected, could result in failure of 

a blade and subsequent loss of control 

of the helicopter. 

Since issuing that AD, bond failures 

continue to be found in certain blades 

produced under a Parts Manufacturer 

Approval based on STC SH778GL. 

These bond failures occurred even after 

the inspections specified by Rotor 

Trends LLC Service Bulletin (SB) No. 

01.03, dated July 9, 2003 (Rotor Trends 

SB), and required by AD 2003–15–51. 

Pflight of Phancy Corp. (PPC), the 

current STC holder, has issued Service 

Bulletin No. SB L3160–P–001, dated 

May 20, 2009 (PPC SB), to supersede the 

Rotor Trends SB. The PPC SB specifies 

visual and tap inspections of the blade 

root fittings and doublers. The PPC SB 

also specifies replacing certain blades 

that have voids or paint cracks and 

inspecting the blade tip weight housing 

on the outboard end of the blade. 

Finally, the PPC SB specifies removing 

all affected blades by May 20, 2010, or 

500 hours time-in-service (TIS), 

whichever occurs first. This AD does 

not require replacing the blades at 500 

hours TIS. However, replacing the 

affected blades with airworthy blades to 

which this AD does not apply would be 

terminating action for the requirements 

of this AD. 

Since an unsafe condition has been 

identified that is likely to exist or 

develop on other Eurocopter model 

helicopters of these same type designs, 

this AD supersedes AD 2003–15–51 to 

require the following: 

• Within 10 hours TIS, inspect each 

affected blade in the doublers for a void 

and in the forward and aft edges for a 

paint crack. 

Æ If you do not find a void or paint 

crack in the doublers or fitting, and the 

only void you find is isolated in a .25 

inch edge band of any doubler or a 

fitting, repeat the inspection at intervals 

not to exceed 30 hours TIS. 

Æ If you find a void in any doubler or 

either fitting not isolated in a .25 inch 

band or a paint crack of any length 

along the forward or aft edge of the 

fitting at certain blade stations, replace 

the blade with an airworthy blade before 

further flight. 

• Within 10 hours TIS, tap and 

visually inspect each affected blade: 

Æ Remove the paint, and coin tap 

inspect the upper and lower surface of 

the No. 2 spar to tip weight housing 

bond for a bond void. 

Æ Using a 10X or higher magnifying 

glass, visually inspect the No. 1 spar 

around through pins for hole elongation, 

a crack in the spar, and pin movement 

(pins should be flush with upper and 

lower spar surfaces). Visually inspect 

the tip weight housing outboard face for 

movement relative to the spar (tip 

weight housing should be flush with the 

face of No. 1 and 2 spars). 

Æ Measure the thickness of the upper 

and lower spar by using calipers held 

against the face of the No. 1 spar in 

alignment with the through pins. 

Æ If you find any of the following, 

replace the blade with an airworthy 

blade before further flight: 

Æ A void between the No. 2 spar to 

tip weight housing; 

Æ In the No. 1 spar, either a crack, an 

elongated through pin hole, movement 

of a through pin, or a through pin that 

is not flush with the spar surface; 

Æ Movement of the tip weight 

housing or a tip weight housing that is 

not flush with the No. 1 or 2 spar; or 

Æ An upper or lower spar measures 

less than 0.045 inch. 

Æ If you do not find any of these 

discrepancies, repeat the inspection at 

intervals not to exceed 30 hours TIS. 

• Replacing an affected blade with an 

airworthy blade, with a serial number 

that is not included in the 

‘‘Applicability’’ section of this AD, 

constitutes terminating action for the 

requirements of this AD. 

Do the actions by following the 

specified portions of the SB described 

previously. 

The short compliance time involved 

is required because the previously 

described critical unsafe condition can 

adversely affect the controllability or 

structural integrity of the helicopter. 

Therefore, inspecting each blade within 

10 hours TIS, repeating the inspection at 

intervals not to exceed 30 hours TIS, 

and replacing the blades as necessary 

before further flight are very short 

compliance times, and this AD must be 

issued immediately. 

Since a situation exists that requires 

the immediate adoption of this 

regulation, it is found 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. 

The FAA estimates that this AD will 

affect 30 helicopters. The required 

actions will take about 3 work hours to 

inspect a blade and 3 work hours to 

replace a blade at an average labor rate 

of $80 per work hour. Required parts 

will cost about $50,000 per blade. There 

are three blades per helicopter. Based on 

these figures, we estimate the total cost 

impact of the AD on U.S. operators to 

be $3,588,640, assuming 71 blades are 

replaced. 


rmajette on DSK29S0YB1PROD with RULES
4484 Federal Register / Vol. 75, No. 18 / Thursday, January 28, 2010 / Rules and Regulations 

Comments Invited 

This AD is a final rule that involves 

requirements that affect flight safety and 

was not preceded by notice and an 

opportunity for public comment; 

however, we invite you to submit any 

written data, views, or arguments 

regarding this AD. Send your comments 

to an address listed under ADDRESSES. 

Include ‘‘Docket No. FAA–2010–0047; 

Directorate Identifier 2009–SW–28–AD’’ 

at the beginning of your comments. We 

specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

the AD. We will consider all comments 

received by the closing date and may 

amend the AD in light 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 with FAA 

personnel concerning this AD. Using the 

search function of our docket Web site, 

you can find and read the comments to 

any of our dockets, including the name 

of the individual who sent the 

comment. You may review the DOT’s 

complete Privacy Act Statement in the 

Federal Register published on April 11, 

2000 (65 FR 19477–78). 

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 the 

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 an economic evaluation 

of the estimated costs to comply with 

this AD. See the AD docket to examine 

the economic evaluation. 

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 

removing Amendment 39–13276 (68 FR 

51681, dated August 28, 2003), and by 

adding a new airworthiness directive 

(AD), Amendment 39–16177, to read as 

follows: 

2010–02–07 Eurocopter France: 

Amendment 39–16177. Docket No. 

FAA–2010–0047; Directorate Identifier 

2009–SW–28–AD. Supersedes AD 2003– 

15–51, Amendment 39–13276, Docket 

No. 2003–SW–34–AD. 

Applicability: 

Eurocopter France Model SE3160, SA315B, 

SA316B, SA316C, and SA319B helicopters, 

with main rotor blade (blade) part number 

L3160–100–01, serial number (S/N) 600 

through 671 (except those identified with 

both ‘‘SB L3160–P–001A’’ and ‘‘SB L3160–P– 

001B’’ next to the blade data plate), produced 

under a Parts Manufacturer Approval based 

on Supplemental Type Certificate SH778GL, 

installed, certificated in any category. 

Compliance: 

Required as indicated. 

To prevent failure of a blade and 

subsequent loss of control of the helicopter, 

do the following: 

(a) Within 10 hours time-in-service (TIS), 

unless accomplished previously, tap and 

visually inspect each blade, S/N 600 through 

666, 668 through 669, and 671 (except those 

identified with ‘‘SB L3160–P–001A’’ next to 

the blade data plate) in the root doublers for 

a void and in the forward and aft edges for 

a paint crack in the areas depicted in Figure 

1 of Phlight of Phancy Corp. Service Bulletin 

No. SB L3160–P–001, dated May 20, 2009 

(SB), and by following the Accomplishment 

Instructions, Part A, paragraph 2.a. through 

2.e., of the SB. 

(1) If there is no void or paint crack in the 

root doublers or fitting, and the only void 

you find is isolated in the .25 inch edge band 

of a doubler or a fitting as depicted in Figure 

1 of the SB, repeat the inspection at intervals 

not to exceed 30 hours TIS. 

(2) If you find a void in any doubler or any 

root fitting not isolated to the .25 inch band 

as depicted in Figure 1 of the SB or a paint 

crack of any length along the forward or aft 

edge of a root fitting between Blade Stations 

35.02 and 42.52, replace the blade with an 

airworthy blade before further flight. 

(b) Within 10 hours TIS, unless 

accomplished previously, inspect each blade, 

S/N 600 through 671 (except those identified 

with ‘‘SB L3160–P–001B’’ next to the blade 

data plate), in the areas depicted in Figures 

2 and 3 and by following the 

Accomplishment Instructions, Part B, of the 

SB as follows: 

(1) Remove the paint and coin tap inspect 

the upper and lower surface of the No. 2 spar 

to tip weight housing bond as depicted in 

Figure 2 of the SB for a bond void. Conduct 

the inspection by following the 

Accomplishment Instructions, Part B, 

paragraphs 2.a. through 2.e. of the SB. 

(2) Using a 10X or higher magnifying glass, 

visually inspect the No. 1 spar around the 

through pins for hole elongation, a crack in 

the spar, and pin movement (pins should be 

flush with upper and lower spar surfaces). 

Visually inspect the tip weight housing 

outboard face for evidence of movement 

relative to the spar (tip weight housing 

should be flush with the face of No. 1 and 

2 spars). 

(3) Measure the thickness of the upper and 

lower spar by using calipers held against the 

face of the No. 1 spar in alignment with the 

through pins as depicted in Figure 3 of the 

SB. 

(4) If you find any of the following, replace 

the blade with an airworthy blade before 

further flight: 

(i) A void between the No. 2 spar and tip 

weight housing; 

(ii) In the No. 1 spar, either a crack, an 

elongated through pinhole, movement of a 

through pin, or a through pin that is not flush 

with the spar surface; 

(iii) Movement of the tip weight housing or 

a tip weight housing that is not flush with 

the No. 1 and No. 2 spar; or 

(iv) An upper or lower spar with thickness 

less than 0.045 inch. 

(5) If you do not find any of the 

discrepancies identified in paragraph (b)(4)(i) 

through (b)(4)(iv) of this AD, repeat the 

inspections required by paragraph (b) of this 

AD at intervals not to exceed 30 hours TIS. 

(c) Replacing an affected blade with an 

airworthy blade with a serial number that is 

not included in the ‘‘Applicability’’ section of 


rmajette on DSK29S0YB1PROD with RULES
Federal Register / Vol. 75, No. 18 / Thursday, January 28, 2010 / Rules and Regulations 4485 

this AD constitutes terminating action for the 

requirements of this AD. 

(d) 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, Rotorcraft 

Directorate, Rotorcraft Certification Office, 

ATTN: DOT/FAA Southwest Region, Martin 

Crane, ASW–170, Aviation Safety Engineer, 

2601 Meacham Blvd., Fort Worth, Texas 

76137, telephone (817) 222–5170, fax (817) 

222–5783, for information about previously 

approved alternative methods of compliance. 

(e) Special flight permits will not be 

issued. 

(f) The Joint Aircraft System/Component 

(JASC) Code for the subject of this AD is 

Code 6210: Main rotor blades. 

(g) Inspect the blades by following the 

specified portions of the Phlight of Phancy 

Corp. Service Bulletin SB L3160–P–001, 

dated May 20, 2009. The Director of the 

Federal Register approved this incorporation 

by reference under 5 U.S.C. 552(a) and 1 CFR 

part 51. Copies may be obtained from Phlight 

of Phancy Corp., 791 Westport Parkway, Fort 

Worth, Texas 76177–4511, telephone 817– 

491–6755, fax 817–491–6759. 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. 

(h) This amendment becomes effective on 

February 12, 2010. 

Issued in Fort Worth, Texas, on January 8, 

2010. 

Mark R. Schilling, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–1157 Filed 1–27–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0793; Directorate 

Identifier 2009–NM–051–AD; Amendment 

39–16183; AD 2010–02–12] 

RIN 2120–AA64 

Airworthiness Directives; Fokker 

Services B.V. Model F.28 Mark 0070 

and 0100 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: 

Several cases have been reported where a 

passenger door actuator detached from the 

passenger door. This caused the passenger 

door to drop to the platform in an 

uncontrolled manner. 

This condition, if not corrected, could 

result in injury to persons on the ground and 

damage to the aircraft. 

* * * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

March 4, 2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of March 4, 2010. 

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 September 28, 2009 (74 FR 

49349). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

Several cases have been reported where a 

passenger door actuator detached from the 

passenger door. This caused the passenger 

door to drop to the platform in an 

uncontrolled manner. 

This condition, if not corrected, could 

result in injury to persons on the ground and 

damage to the aircraft. 

To address this problem, Fokker Services 

has developed an improved actuator to 

ensure the proper functioning of the door 

opening mechanism. 

For the reason described above, this AD 

requires the replacement of existing airstair 

door actuators with improved actuators. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Explanation of Changes Made to This 

AD 

We have revised this AD to identify 

the legal name of the manufacturer as 

published in the most recent type 

certificate data sheet for the affected 

airplane models. 

Conclusion 

We reviewed the available data, and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously. 

We determined that these changes will 

not increase the economic burden on 

any operator or increase the scope of the 

AD. 

Differences Between This AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have required different 

actions in this AD from those in the 

MCAI in order to follow our FAA 

policies. Any such differences are 

highlighted in a Note within the AD. 

Costs of Compliance 

We estimate that this AD will affect 2 

products of U.S. registry. We also 

estimate that it will take about 12 workhours per product to comply with the 

basic requirements of this AD. The 

average labor rate is $80 per work-hour. 

Required parts will cost about $4,933 

per product. Where the service 

information lists required parts costs 

that are covered under warranty, we 

have assumed that there will be no 

charge for these parts. As we do not 

control warranty coverage for affected 

parties, some parties may incur costs 

higher than estimated here. Based on 

these figures, we estimate the cost of 

this AD to the U.S. operators to be 

$11,786, or $5,893 per product. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 


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