This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by

the Superintendent of Documents. Prices of

new books are listed in the first FEDERAL

REGISTER issue of each week.

Rules and Regulations Federal Register

2055 

Vol. 75, No. 9 

Thursday, January 14, 2010 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0763; Directorate 

Identifier 2007–NM–301–AD; Amendment 

39–16170; AD 2010–01–11] 

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: 

Excessive wear and tear of the backlash 

remover mechanism has been found several 

times on Goodrich Part Number (P/N) 23400– 

3B and P/N 23400–7 elevator booster control 

units (BCU), while corrosion has been found 

on some components in other BCU. The wear 

and tear may result in a (partly) blocked 

operation of the elevator system in the 

normal (hydraulic) mode, while any 

corrosion may result in deteriorated elevator 

control when the BCU is in MANUAL mode. 

* * * * * 

The unsafe condition is wear and tear, 

and corrosion of the backlash remover 

mechanism, which can cause a (partly) 

blocked operation of the elevator system 

in the normal (hydraulic) mode and 

deteriorated elevator control when the 

BCU is in MANUAL mode, which could 

result in loss of control of the airplane. 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

February 18, 2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of February 18, 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 1, 2009 (74 FR 

45139). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

Excessive wear and tear of the backlash 

remover mechanism has been found several 

times on Goodrich Part Number (P/N) 23400– 

3B and P/N 23400–7 elevator booster control 

units (BCU), while corrosion has been found 

on some components in other BCU. The wear 

and tear may result in a (partly) blocked 

operation of the elevator system in the 

normal (hydraulic) mode, while any 

corrosion may result in deteriorated elevator 

control when the BCU is in MANUAL mode. 

Fokker Services and Goodrich determined 

that modification of the affected elevator 

BCU in accordance with Goodrich 

Component Service Bulletin (CSB) 23400– 

27–27 would correct this situation. * * * 

[I]t has been decided to require the 

inspection of aircraft fitted with BCU P/N 

23400–3 and P/N 23400–5 (serial numbers 

MC–001 through MC–288) and the 

modification of these units in accordance 

with Goodrich CSB 23400–27–15 (P/N 

change from 23400–3 to 23400–3B, or from 

23400–5 to 23400–7, as applicable). 

Previously, CAA–Netherlands AD (BLA) 

93–051/3 dated 29 April 1994 [which 

corresponds to FAA AD 97–03–09] was 

issued, which requires a periodic inspection 

of P/N 23400–3 and P/N 23400–5 elevator 

BCU that could be affected by corrosion, and 

allows modification of the BCU in 

accordance with Fokker Service Bulletin 

SBF100–27–061 (application of Goodrich 

CSB 23400–27–15) as (optional) terminating 

action for these inspections. 

* * * In addition, this AD requires the 

eventual replacement of all affected elevator 

BCU with modified units. 

This new AD does not cancel the repetitive 

inspection requirements of CAA–NL AD 

(BLA) 93–051/3 for BCU P/N 23400–3 and 

P/N 23400–5 as long as these remain 

installed on any in-service aircraft. 

The unsafe condition is wear and tear, 

and corrosion of the backlash remover 

mechanism, which can cause a (partly) 

blocked operation of the elevator system 

in the normal (hydraulic) mode and 

deteriorated elevator control when the 

BCU is in MANUAL mode, which could 

result in loss of control of the airplane. 

The required actions include inspecting 

the backlash remover of the elevator 

booster control unit to determine the 

displacement of the pivot bolt; and if 

necessary, replacing the elevator booster 

control unit. Depending on the 

measurement of the displacement, the 

compliance time for replacement ranges 

from before further flight to 3,000 flight 

cycles. 

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. 


wwoods2 on DSK1DXX6B1PROD with RULES_PART 1
2056 Federal Register / Vol. 75, No. 9 / Thursday, January 14, 2010 / Rules and Regulations 

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 13 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 $189 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 $2,458, or 

$1,229 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 

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 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 this AD: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

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

3. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

Examining the AD Docket 

You may examine the AD docket 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 AD docket 

contains the NPRM, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (telephone 

(800) 647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

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: 

2010–01–11 Fokker Services B.V.: 

Amendment 39–16170. Docket No. 

FAA–2009–0763; Directorate Identifier 

2007–NM–301–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective February 18, 2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Fokker Services B.V. 

Model F.28 Mark 0070 and Mark 0100 

airplanes, all serial numbers, certificated in 

any category. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 27: Flight Controls. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

Excessive wear and tear of the backlash 

remover mechanism has been found several 

times on Goodrich Part Number (P/N) 23400– 

3B and P/N 23400–7 elevator booster control 

units (BCU), while corrosion has been found 

on some components in other BCU. The wear 

and tear may result in a (partly) blocked 

operation of the elevator system in the 

normal (hydraulic) mode, while any 

corrosion may result in deteriorated elevator 

control when the BCU is in MANUAL mode. 

Fokker Services and Goodrich determined 

that modification of the affected elevator 

BCU in accordance with Goodrich 

Component Service Bulletin (CSB) 23400– 

27–27 would correct this situation. * * * 

[I]t has been decided to require the 

inspection of aircraft fitted with BCU P/N 

23400–3 and P/N 23400–5 (serial numbers 

MC–001 through MC–288) and the 

modification of these units in accordance 

with Goodrich CSB 23400–27–15 (P/N 

change from 23400–3 to 23400–3B, or from 

23400–5 to 23400–7, as applicable). 

Previously, CAA–Netherlands AD (BLA) 

93–051/3 dated 29 April 1994 [which 

corresponds to FAA AD 97–03–09] was 

issued, which requires a periodic inspection 

of P/N 23400–3 and P/N 23400–5 elevator 

BCU that could be affected by corrosion, and 

allows modification of the BCU in 

accordance with Fokker Service Bulletin 

SBF100–27–061 (application of Goodrich 

CSB 23400–27–15) as (optional) terminating 

action for these inspections. 

* * * In addition, this AD requires the 

eventual replacement of all affected elevator 

BCU with modified units. 

This new AD does not cancel the repetitive 

inspection requirements of CAA–NL AD 

(BLA) 93–051/3 for BCU P/N 23400–3 and 

P/N 23400–5 as long as these remain 

installed on any in-service aircraft. 

The unsafe condition is wear and tear, and 

corrosion of the backlash remover 

mechanism, which can cause a (partly) 

blocked operation of the elevator system in 

the normal (hydraulic) mode and 

deteriorated elevator control when the BCU 

is in MANUAL mode, which could result in 

loss of control of the airplane. The required 

actions include inspecting the backlash 

remover of the elevator booster control unit 

to determine the displacement of the pivot 

bolt; and if necessary, replacing the elevator 

booster control unit. Depending on the 

measurement of the displacement, the 

compliance time for replacement ranges from 

before further flight to 3,000 flight cycles. 

Actions and Compliance 

(f) Unless already done, do the following 

actions. 


wwoods2 on DSK1DXX6B1PROD with RULES_PART 1
Federal Register / Vol. 75, No. 9 / Thursday, January 14, 2010 / Rules and Regulations 2057 

(1) For airplanes equipped with booster 

control unit P/N 23400–3B, 23400–7, 23400– 

3, or 23400–5, within 12 months after the 

effective date of this AD, perform a one-time 

inspection of the elevator booster control unit 

in accordance with Part 1 of the 

Accomplishment Instructions of Fokker 

Service Bulletin SBF100–27–088, dated June 

4, 2007. 

(2) At the time specified in Table 1 of this 

AD, and depending on the result of the 

inspection required by paragraph (f)(1) of this 

AD, replace the elevator booster control unit 

with a modified unit having P/N 23400–3B 

or P/N 23400–7, in accordance with Part 2 of 

the Accomplishment Instructions of Fokker 

Service Bulletin SBF100–27–088, dated June 

4, 2007. The replacement part must be 

modified in accordance with Goodrich 

Service Bulletin 23400–27–27, Revision 1, 

dated September 14, 2007. 

TABLE 1—REPLACEMENT PARAMETERS

Dimension A Replace within 

A < 0.12 millimeters 

(mm).

Not applicable. 

0.12 mm ≤ A < 0.5 

mm.

3,000 flight cycles. 

0.5 mm ≤ A < 1.0 mm 2,000 flight cycles. 

1.0 mm ≤ A < 1.5 mm 1,000 flight cycles. 

1.5 mm ≤ A < 2.0 mm 500 flight cycles. 

2.0 mm ≤ A < 2.5 mm 125 flight cycles. 

A ≥ 2.5 mm ............... Before further flight. 

(3) Within 60 months after the effective 

date of this AD, replace all remaining 

unmodified elevator booster control units 

having P/N 23400–3B or 

P/N 23400–7 with modified units, in 

accordance with Part 2 of the 

Accomplishment Instructions of Fokker 

Service Bulletin SBF100–27–088, dated June 

4, 2007. The replacement part must be 

modified in accordance with Goodrich 

Service Bulletin 23400–27–27, Revision 1, 

dated September 14, 2007. 

(4) Within 60 months after the effective 

date of this AD, replace all remaining 

elevator booster control units having P/N 

23400–3 or P/N 23400–5 with modified units 

having P/N 23400–3B or P/N 23400–7, in 

accordance with Part 2 of the 

Accomplishment Instructions of Fokker 

Service Bulletin SBF100–27–088, dated June 

4, 2007. The replacement part must be 

modified in accordance with Goodrich 

Service Bulletin 23400–27–27, Revision 1, 

dated September 14, 2007. 

(5) As of 12 months after the effective date 

of this AD, no person may install a Goodrich 

P/N 23400–3B, P/N 23400–7, P/N 23400–3 or 

P/N 23400–5 elevator booster control unit on 

any airplane, unless the conditions of 

paragraph (f)(5)(i) or (f)(5)(ii), as applicable, 

are met. 

(i) The unit has been inspected in 

accordance with paragraph (f)(1) of this AD, 

and the applicable action(s) required by 

paragraph (f)(2) is accomplished at the time 

specified in that paragraph. 

(ii) The unit having P/N 23400–3B or P/N 

23400–7 has been modified in accordance 

with Goodrich Service Bulletin 23400–27–27, 

Revision 1, dated September 14, 2007. 

(6) As of 60 months after the effective date 

of this AD, no person may install a Goodrich 

P/N 23400–3 or P/N 23400–5 elevator booster 

control unit on any airplane. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(g) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, 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: 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. Before using 

any approved AMOC on any airplane to 

which the AMOC applies, notify your 

principal maintenance inspector (PMI) or 

principal avionics inspector (PAI), as 

appropriate, or lacking a principal inspector, 

your local Flight Standards District Office. 

The AMOC approval letter must specifically 

reference this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, under the 

provisions of the Paperwork Reduction Act 

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

Management and Budget (OMB) has 

approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(h) Refer to MCAI European Aviation 

Safety Agency Airworthiness Directive 2009– 

0032, dated February 17, 2009; Fokker 

Service Bulletin SBF100–27–088, dated June 

4, 2007; and Goodrich Service Bulletin 

23400–27–27, Revision 1, dated September 

14, 2007; for related information. 

Material Incorporated by Reference 

(i) You must use Fokker Service Bulletin 

SBF100–27–088, dated June 4, 2007; and 

Goodrich Service Bulletin 23400–27–27, 

Revision 1, dated September 14, 2007; 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 Fokker service information 

identified in this AD, contact Fokker Services 

B.V., Technical Services Dept., P.O. Box 231, 

2150 AE Nieuw-Vennep, the Netherlands; 

telephone +31 (0)252–627–350; fax +31 

(0)252 627 211; e-mail 

technicalservices.fokkerservices@stork.com; 

Internet http://www.myfokkerfleet.com. 

(3) For Goodrich service information 

identified in this AD, contact Goodrich 

Corporation, Landing Gear, 1400 South 

Service Road, West Oakville L6L 5Y7, 

Ontario, Canada; telephone 905–825–1568; 

e-mail jean.breed@goodrich.com; Internet 

http://www.goodrich.com/TechPubs. 

(4) 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. 

(5) 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 

December 28, 2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–102 Filed 1–13–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–1251; Directorate 

Identifier 2009–NM–133–AD; Amendment 

39–16174; AD 2010–02–03] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A340–200 and A340–300 Series 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

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: 

* * * * * 

Engineering analysis using the new 

calculated loads has shown that the 

structural integrity of the forward engine 

mount cannot be guaranteed after either 

thrust link has accumulated 15500 Flight 

Cycles (FC). 

* * * * * 


wwoods2 on DSK1DXX6B1PROD with RULES_PART 1