Federal Register / Vol. 72, No. 38 / Tuesday, February 27, 2007 / Rules and Regulations 8615 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Model R2160 

airplanes, serial numbers 001 through 378, 

certificated in any category. 

Reason 

(d) The mandatory continuing 

airworthiness information (MCAI) states that 

there have been instances indicating that 

production aircraft may not have a metal 

barrier between the cabin and the fuel tank 

bay. Lack of a barrier could allow flammable 

fuel vapors to enter the cabin. The MCAI 

requires that, to ensure that the aircraft is in 

compliance with 14 CFR 23.967(d), inspect 

the aircraft to determine if a metal barrier is 

installed behind the seats and, if not 

installed, to manufacture and install a 

barrier. 

Actions and Compliance 

(e) Unless already done, do the following 

actions within the next 100 hours time-inservice or within 6 months after April 3, 2007 

(the effective date of this AD), whichever 

occurs first. 

(1) Inspect the aircraft to determine if a 

metal barrier is installed behind the seats per 

Alpha Aviation Service Bulletin AA–SB–28–

001, dated July 10, 2006. 

(2) If a metal barrier is installed per Alpha 

Aviation Service Bulletin AA–SB–28–001, 

dated July 10, 2006, and (e)(1) of this AD, 

then no further action is required. 

(3) If a metal barrier is not installed, 

manufacture and install a barrier per Alpha 

Aviation Service Bulletin AA–SB–28–001, 

dated July 10, 2006, and Alpha Aviation 

Drawing No. 60–53–119 (page 3 of 3 of the 

Service Bulletin). 

FAA AD Differences 

Note: This AD differs from the MCAI and/ 

or service information as follows: No 

differences. 

Other FAA AD Provisions 

(f) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Staff, 

FAA, ATTN: Karl Schletzbaum, Aerospace 

Engineer, FAA, Small Airplane Directorate, 

901 Locust, Room 301, Kansas City, Missouri 

64106; telephone: (816) 329–4146; fax: (816) 

329–4090, has the authority to approve 

AMOCs for this AD, if requested using the 

procedures found in 14 CFR 39.19. 

(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 

(g) Refer to MCAI Civil Aviation Authority 

of New Zealand AD DCA/R2000/38, dated 

June 29, 2006, for related information. 

Material Incorporated by Reference 

(h) You must use Alpha Aviation Service 

Bulletin AA–SB–28–001, dated July 10, 2006, 

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 Alpha Aviation Ltd, Ingram 

Road, Hamilton Airport RD 2, Hamilton 

2021, New Zealand; telephone: 011 64 7 843 

7070; fax: 011 64 7 843 8040; Internet: http:// 

www.alphaaviation.co.nz. 

(3) You may review copies at the FAA, 

Central Region, Office of the Regional 

Counsel, 901 Locust, Room 506, Kansas City, 

Missouri 64106; 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/ 

cfr/ibr-locations.html. 

Issued in Kansas City, Missouri, on 

February 15, 2007. 

David R. Showers, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E7–3163 Filed 2–26–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–25391; Directorate 

Identifier 2006–NM–097–AD; Amendment 

39–14956; AD 2007–04–23] 

RIN 2120–AA64 

Airworthiness Directives; Fokker 

Model F.28 Mark 0070 and 0100 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD), 

which applies to certain Fokker Model 

F.28 Mark 0070 and 0100 airplanes. 

That AD currently requires a one-time 

inspection of the sliding members in the 

main landing gear (MLG) for cracking 

and replacement of the sliding members 

with serviceable parts if necessary. This 

new AD adds repetitive magnetic 

particle inspections of the sliding 

members of the MLG for cracking and 

corrective actions as necessary. This AD 

results from inspection findings that 

have shown repetitive inspections are 

needed to establish fleet safety. We are 

issuing this AD to detect and correct 

fatigue cracking of the sliding member, 

which could result in possible 

separation of the MLG from the airplane 

and consequent reduced controllability 

of the airplane upon landing and 

possible injury to passengers. 

DATES: This AD becomes effective April 

3, 2007. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of April 3, 2007. 

On May 19, 2004 (69 FR 19759, April 

14, 2004), the Director of the Federal 

Register approved the incorporation by 

reference of Fokker Service Bulletin 

SBF100–32–133, dated April 1, 2002. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

dms.dot.gov or in person at the Docket 

Management Facility, U.S. Department 

of Transportation, 400 Seventh Street 

SW., Nassif Building, Room PL–401, 

Washington, DC. 

Contact Fokker Services B.V., 

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

2150 AE Nieuw-Vennep, the 

Netherlands, for service information 

identified in this AD. 

FOR FURTHER INFORMATION CONTACT: Tom 

Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 227–1137; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Examining the Docket 

You may examine the airworthiness 

directive (AD) docket on the Internet at 

http://dms.dot.gov or in person at the 

Docket Management Facility office 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

The Docket Management Facility office 

(telephone (800) 647–5227) is located on 

the plaza level of the Nassif Building at 

the street address stated in the 

ADDRESSES section. 

Discussion 

The FAA issued a supplemental 

notice of proposed rulemaking (NPRM) 

to amend 14 CFR part 39 to include an 

AD that supersedes AD 2004–08–01, 

amendment 39–13570 (69 FR 19759, 

April 14, 2004). The existing AD applies 

to certain Fokker Model F.28 Mark 0070 

and 0100 airplanes. That supplemental 

NPRM was published in the Federal 

Register on December 28, 2006 (71 FR 

78107). That supplemental NPRM 


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8616 Federal Register / Vol. 72, No. 38 / Tuesday, February 27, 2007 / Rules and Regulations 

proposed to continue to require a onetime inspection of the sliding members 

in the main landing gear (MLG) for 

cracking, and replacement of the sliding 

members with serviceable parts if 

necessary. That supplemental NPRM 

also proposed to require repetitive 

magnetic particle inspections of the 

sliding members of the MLG for 

cracking and corrective actions as 

necessary. That supplemental NPRM 

also revised the original NPRM by 

correcting a certain part number in the 

applicability. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. No comments 

have been received on the supplemental 

NPRM or on the determination of the 

cost to the public. 

Conclusion 

We have carefully reviewed the 

available data and determined that air 

safety and the public interest require 

adopting the AD as proposed by the 

supplemental NPRM. 

Costs of Compliance 

This AD affects about 37 airplanes of 

U.S. registry. 

The inspection that is required by AD 

2004–08–01 and retained in this AD 

takes either about 4 or 12 work hours 

per airplane, depending on airplane 

configuration, at an average labor rate of 

$80 per work hour. Based on these 

figures, the estimated cost of the 

currently required actions for U.S. 

operators is $11,840 or $35,520, or $320 

or $960 per airplane, depending on 

airplane configuration. 

The new required inspections take 

about 2 work hours per airplane, at an 

average labor rate of $80 per work hour. 

Based on these figures, the estimated 

cost of the new inspections specified in 

this AD for U.S. operators is $5,920, or 

$160 per airplane, per inspection 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: 

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 39–13570 (69 

FR 19759, April 14, 2004) and by adding 

the following new airworthiness 

directive (AD): 

2007–04–23 Fokker Services B.V.: 

Amendment 39–14956. Docket No. 

FAA–2006–25391; Directorate Identifier 

2006–NM–097–AD. 

Effective Date 

(a) This AD becomes effective April 3, 

2007. 

Affected ADs 

(b) This AD supersedes AD 2004–08–01. 

Applicability 

(c) This AD applies to Fokker Model F.28 

Mark 0070 and 0100 airplanes, certificated in 

any category; equipped with any Dowty or 

Messier-Dowty main landing gear (MLG) 

listed in Table 1 of this AD. 

TABLE 1.—AFFECTED PARTS

MLG part number

(P/N)—

Equipped with sliding 

member P/N—

201072011 ................ 201072301 or 

201072305 

201072012 ................ 201072301 or 

201072305 

201072013 ................ 201072301 or 

201072305 

201072014 ................ 201072301 or 

201072305 

201072015 ................ 201072301 or 

201072305 

201072016 ................ 201072301 or 

201072305 

Unsafe Condition 

(d) This AD results from inspection 

findings that have shown repetitive 

inspections are needed to establish fleet 

safety. We are issuing this AD to detect and 

correct fatigue cracking of the sliding 

member, which could result in possible 

separation of the MLG from the airplane and 

consequent reduced controllability of the 

airplane upon landing and possible injury to 

passengers. 

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. 

Requirements of AD 2004–08–01 

Inspection and Replacement if Necessary 

(f) Within 1,000 flight cycles or 6 months 

after May 19, 2004 (the effective date of AD 

2004–08–01), whichever occurs first, perform 

a magnetic inspection of the sliding members 

of the MLG for cracking, in accordance with 

the Accomplishment Instructions of Fokker 

Service Bulletin SBF100–32–133, dated April 

1, 2002. If any crack is found during the 

inspection, before further flight, replace the 

sliding members with serviceable parts in 

accordance with the Accomplishment 

Instructions of the service bulletin. 

Note 1: Fokker Service Bulletin SBF100–

32–133, dated April 1, 2002, refers to 

Messier-Dowty Service Bulletin F100–32–

103, dated March 11, 2002, as an additional 

source of service information. 

Parts Installation With Accomplishment of 

New Service Bulletins 

(g) As of May 19, 2004, no person may 

install a sliding member of the MLG, 

P/N 201072301 or P/N 201072305, on any 

airplane, unless it has been inspected in 

accordance with the Accomplishment 

Instructions of Fokker Service Bulletin 

SBF100–32–133, dated April 1, 2002; Fokker 


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Federal Register / Vol. 72, No. 38 / Tuesday, February 27, 2007 / Rules and Regulations 8617 

Service Bulletin SBF100–32–139, dated 

March 5, 2004; or Fokker Service Bulletin 

SBF100–32–144, dated September 19, 2005; 

and found to be serviceable. 

Note 2: Fokker Service Bulletin SBF100–

32–139, dated March 5, 2004, refers to 

Messier-Dowty Service Bulletin F100–32–

105, dated March 2, 2004, as an additional 

source of service information for 

accomplishing a magnetic inspection. 

Note 3: Fokker Service Bulletin SBF100–

32–144, dated September 19, 2005, refers to 

Messier-Dowty Service Bulletin F100–32–

110, dated August 25, 2005, as an additional 

source of service information for 

accomplishing a magnetic inspection. 

Reporting Requirement Difference 

(h) Although Fokker Service Bulletin 

SBF100–32–133, dated April 1, 2002, 

specifies to submit certain information to the 

manufacturer, this AD does not include such 

a requirement. 

New Requirements of this AD 

Repetitive Inspections 

(i) At the later of the compliance times 

specified in paragraphs (i)(1) and (i)(2) of this 

AD: Do a magnetic inspection of the sliding 

members of the left and right MLG for 

cracking, and do all corrective actions before 

further flight after the inspection, by 

accomplishing all of the applicable actions 

specified in the Accomplishment 

Instructions of Fokker Service Bulletin 

SBF100–32–144, dated September 19, 2005. 

Repeat the inspection thereafter at intervals 

not to exceed 2,000 flight cycles. 

(1) Within 2,000 flight cycles after 

accomplishing paragraph (f) of this AD. 

(2) Within 4 months after the effective date 

of this AD. 

Credit for Fokker Service Bulletin SBF100– 

32–139 

(j) Actions done before the effective date of 

this AD in accordance with Fokker Service 

Bulletin SBF100–32–139, dated March 5, 

2004, are acceptable for compliance with the 

corresponding requirements of paragraph (f) 

of this AD. 

Alternative Methods of Compliance (AMOCs) 

(k)(1) The Manager, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, has the authority to approve AMOCs 

for this AD, if requested in accordance with 

the procedures found in 14 CFR 39.19. 

(2) Before using any AMOC approved in 

accordance with § 39.19 on any airplane to 

which the AMOC applies, notify the 

appropriate principal inspector in the FAA 

Flight Standards Certificate Holding District 

Office. 

Related Information 

(l) Dutch airworthiness directive NL–2005–

012, dated October 17, 2005, also addresses 

the subject of this AD. 

Material Incorporated by Reference 

(m) You must use the service information 

identified in Table 2 of this AD, as 

applicable, to perform the actions that are 

required by this AD, unless the AD specifies 

otherwise. 

TABLE 2.—MATERIAL INCORPORATED

BY REFERENCE

Fokker service 

bulletin Date 

SBF100–32–133 ....... April 1, 2002. 

SBF100–32–139 ....... March 5, 2004. 

SBF100–32–144 ....... September 19, 2005. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

Fokker Service Bulletin SBF100–32–139, 

dated March 5, 2004; and Fokker Service 

Bulletin SBF100–32–144, dated September 

19, 2005; in accordance with 5 U.S.C. 552(a) 

and 1 CFR part 51. 

(2) On May 19, 2004 (69 FR 19759, April 

14, 2004), the Director of the Federal Register 

approved the incorporation by reference of 

Fokker Service Bulletin SBF100–32–133, 

dated April 1, 2002. 

(3) Contact Fokker Services B.V., Technical 

Services Dept., P.O. Box 231, 2150 AE 

Nieuw-Vennep, the Netherlands, for a copy 

of this service information. You may review 

copies at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington; 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/ 

cfr/ibr-locations.html. 

Issued in Renton, Washington, on February 

13, 2007. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E7–2974 Filed 2–26–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–26355; Directorate 

Identifier 2006–NM–198–AD; Amendment 

39–14953; AD 2007–04–21] 

RIN 2120–AA64 

Airworthiness Directives; Fokker 

Model F.28 Mark 0070 and 0100 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for all 

Fokker Model F.28 Mark 0070 and 0100 

airplanes. This AD requires a one-time 

inspection of the fuel lines located in 

the left and right main landing gear 

(MLG) bays to determine the clearance 

between the fuel and hydraulic lines. If 

necessary, this AD also requires an 

inspection of fuel lines for chafing, the 

replacement of a chafed fuel line with 

a new fuel line, and the repositioning of 

existing clamps and installation of 

additional clamps between the fuel and 

hydraulic lines. This AD results from a 

fuel leak found in the left MLG bay. We 

are issuing this AD to detect and correct 

inadequate clearance between fuel and 

hydraulic lines in the MLG bay, which 

could lead to chafing of a fuel line and 

fuel leakage. A fuel leak near hot brakes 

could result in a fire in the MLG bay. 

DATES: This AD becomes effective April 

3, 2007. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of April 3, 2007. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

dms.dot.gov or in person at the Docket 

Management Facility, U.S. Department 

of Transportation, 400 Seventh Street 

SW., Nassif Building, Room PL–401, 

Washington, DC. 

Contact Fokker Services B.V., 

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

2150 AE Nieuw-Vennep, the 

Netherlands, for service information 

identified in this AD. 

FOR FURTHER INFORMATION CONTACT: Tom 

Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 227–1137; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Examining the Docket 

You may examine the airworthiness 

directive (AD) docket on the Internet at 

http://dms.dot.gov or in person at the 

Docket Management Facility office 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

The Docket Management Facility office 

(telephone (800) 647–5227) is located on 

the plaza level of the Nassif Building at 

the street address stated in the 

ADDRESSES section. 

Discussion 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to all Fokker Model F.28 Mark 

0070 and 0100 airplanes. That NPRM 

was published in the Federal Register 

on November 20, 2006 (71 FR 67077). 

That NPRM proposed to require a onetime inspection of the fuel lines located 

in the left and right main landing gear 

bays to determine the clearance between 

the fuel and hydraulic lines. If 

necessary, that NPRM proposed to 

require an inspection of fuel lines for 


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