59726 Federal Register / Vol. 77, No. 190 / Monday, October 1, 2012 / Rules and Regulations 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0589; Directorate 

Identifier 2011–NM–189–AD; Amendment 

39–17199; AD 2012–19–04] 

RIN 2120–AA64 

Airworthiness Directives; Fokker 

Services B.V. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding two 

existing airworthiness directives (ADs) 

for certain Fokker Services B.V. Model 

F.28 Mark 0100 airplanes. The first 

existing AD currently requires removing 

the actuator from the fuel-balance 

transfer-valve (FBTV) and installing a 

locking device on the FBTV. The second 

existing AD currently requires 

inspecting to verify that the position 

indicator of the FBTV is in the closed 

position and deactivating the fuelbalance transfer-system. This new AD 

requires installing an FBTV locking 

device. This AD was prompted by 

reports that the FBTV was inadvertently 

reactivated after required de-activation 

measures were undone. We are issuing 

this AD to prevent fuel starvation and a 

consequent double-engine flameout, 

possibly resulting in a forced landing, 

damage to the airplane, and injury to 

occupants. 

DATES: This AD becomes effective 

November 5, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of November 5, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication, listed in 

this AD as of April 29, 1996 (61 FR 

14014, March 29, 1996). 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication, listed in 

this AD as of August 10, 1994 (59 FR 

35237, July 11, 1994). 

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, WA 

98057–3356; phone: (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 June 6, 2012 (77 FR 33332), 

and proposed to supersede AD 94–14– 

05, Amendment 39–8957 (59 FR 35237, 

July 11, 1994); and AD 96–07–06, 

Amendment 39–9555 (61 FR 14014, 

March 29, 1996). That NPRM proposed 

to correct an unsafe condition for the 

specified products. The MCAI states: 

Some Fokker F28 Mark 0100 (Fokker 100) 

aeroplanes were delivered from the 

production line with a Fuel-Balance 

Transfer-System (FBTS) installed. Other 

Fokker 100 aeroplanes were delivered with 

only FBTS provisions and for some of those, 

an option existed for in-service activation of 

the FBTS, through Fokker Service Bulletin 

(SB) SBF100–28–021. 

The FBTS was designed to be used during 

maintenance activities to move the Centre of 

Gravity (CG) forward by transferring fuel 

from the main tanks to the centre tank 

through the crossfeed system and a FuelBalance Transfer-Valve (FBTV). 

In 1993, a dormant failure mode was 

discovered, which could lead to fuel 

starvation and consequently to a double 

engine flame-out, possibly resulting in a 

forced landing, damage to the aeroplane and 

injury to occupants. To address and correct 

this unsafe condition, CAA–NL [Civil 

Aviation Authority—Netherlands] issued AD 

BLA 93–160, which required modification of 

the FBTV (Fokker SBF100–28–029) [which 

corresponds to FAA AD 94–14–05, 

Amendment 39–8957 (59 FR 35237, July 11, 

1994)], and later BLA 94–146, which 

required deactivation of the FBTS (Fokker 

SBF100–28–030) [which corresponds to FAA 

AD 96–07–06, Amendment 39–9555 (61 FR 

14014, March 29, 1996)]. 

Recently, one operator reported that on two 

aeroplanes, the FBTS had inadvertently been 

reactivated. SBF100–28–030 had been 

accomplished on both aeroplanes but 

apparently, (some of) the de-activation 

measures introduced with that SB were later 

made undone. Subsequent investigation also 

showed that Fokker SBF100–28–021, 

containing instructions for activating the 

FBTS, had inadvertently been left active 

when SBF100–28–029 and SBF100–28–030 

were published. To address this safety 

concern, Fokker Services have issued 

SBF100–28–066, which introduces a task to 

deactivate the FBTS to a greater extent than 

previously required. At the same time, 

SBF100–28–021 has been cancelled by its 

Revision 1. 

For the reasons described above, this 

[European Aviation Safety Agency (EASA)] 

AD retains the requirements of CAA–NL 

[airworthiness directives] BLA 93–160 and 

BLA 94–146, which are superseded, and 

requires the accomplishment of additional 

measures to deactivate the FBTS [modify the 

airplane by installing an FBTV locking 

device], in accordance with the instructions 

of Fokker Services SBF100–28–066. 

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 (77 

FR 33332, June 6, 2012) or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed—except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (77 FR 

33332, June 6, 2012) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (77 FR 33332, 

June 6, 2012). 

Costs of Compliance 

We estimate that this AD will affect 2 

products of U.S. registry. 

The actions that were required by AD 

94–14–05, Amendment 39–8957 (59 FR 

35237, July 11, 1994), and retained in 

this AD take about 1 work-hour per 

product, at an average labor rate of $85 

per work hour. Required parts cost 

about $250 per product. Based on these 

figures, the estimated cost of the 

currently required actions is $335 per 

product. 

The actions required by AD 96–07–06, 

Amendment 39–9555 (61 FR 14014, 

March 29, 1996), and retained in this 

AD take about 1 work-hour per product, 

at an average labor rate of $85 per work 

hour. Required parts cost about $0 per 

product. Based on these figures, the 

estimated cost of the currently required 

actions is $85 per product. 

We also estimate that it will take 

about 5 work-hours per product to 

comply with the new basic 

requirements of this AD. The average 

labor rate is $85 per work-hour. 

Required parts will cost about $650 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 

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Federal Register / Vol. 77, No. 190 / Monday, October 1, 2012 / Rules and Regulations 59727 

figures, we estimate the cost of this AD 

to the U.S. operators to be $2,150, or 

$1,075 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 that 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); 

3. Will not affect intrastate aviation in 

Alaska; and 

4. 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 (77 FR 33332, June 

6, 2012), 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 

removing airworthiness directive AD 

94–14–05, Amendment 39–8957 (59 FR 

35237, July 11, 1994); and AD 96–07– 

06, Amendment 39–9555 (61 FR 14014, 

March 29, 1996); and adding the 

following new AD: 

2012–19–04 Fokker Services B.V.: 

Amendment 39–17199. Docket No. 

FAA–2012–0589; Directorate Identifier 

2012–NM–189–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective November 5, 2012. 

(b) Affected ADs 

This AD supersedes AD 94–14–05, 

Amendment 39–8957 (59 FR 35237, July 11, 

1994); and AD 96–07–06, Amendment 39– 

9555 (61 FR 14014, March 29, 1996). 

(c) Applicability 

This AD applies to Fokker Services B.V. 

Model F.28 Mark 0100 airplanes; certificated 

in any category; serial numbers 11257, 11258, 

11261, 11262, 11264, 11265, 11266, 11284, 

11285, 11287, 11288, 11290, 11292, 11294, 

11296, 11298, 11299, 11301, 11302, 11304, 

11305, 11307, 11309, 11311, 11315, 11317, 

11319, 11320, 11322, 11336, 11339, 11341 

through 11344 inclusive, 11347, 11348, 

11350, 11351, 11362, 11363, 11364, 11371, 

11374, 11375, 11382, 11383, 11384, 11389, 

11390, 11394, 11400, 11401, 11409, 11410, 

11420 through 11424 inclusive, 11429, 

11430, 11431, 11433, 11441 through 11456 

inclusive, 11461, 11462, 11463, 11470 

through 11475 inclusive, 11477, 11484, 

11485, 11486, 11488, 11489, 11496, 11497, 

11500, 11503, 11505, 11511, 11512, 11516, 

11517, 11518, and 11527. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 28: Fuel. 

(e) Reason 

This AD was prompted by reports that the 

fuel-balance transfer-valve (FBTV) was 

inadvertently reactivated after required deactivation measures were undone. We are 

issuing this AD to prevent fuel starvation and 

a consequent double-engine flameout, 

possibly resulting in a forced landing, 

damage to the airplane, and injury to 

occupants. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Retained Installation of a Locking Device 

for the FBTV 

This paragraph restates the requirements of 

paragraph (a) of AD 94–14–05, Amendment 

39–8957 (59 FR 35237, July 11, 1994). For 

airplanes having serial numbers 11443, 

11446 through 11449 inclusive, and 11456: 

Within 30 days after August 10, 1994 (the 

effective date of AD 94–14–05), remove the 

actuator from the FBTV, part number (P/N) 

7933141J and install a locking device on the 

FBTV, in accordance with the 

Accomplishment Instructions of Fokker 

Service Bulletin SBF100–28–029, Revision 1, 

dated November 30, 1993. 

(h) Retained Inspection and Deactivation 

(1) This paragraph restates the 

requirements of paragraphs (a) and (b) of AD 

96–07–06, Amendment 39–9555 (61 FR 

14014, March 29, 1996). For airplanes 

identified in Fokker Service Bulletin 

SBF100–28–030, Revision 1, dated December 

5, 1994: After April 29, 1996 (the effective 

date of AD 96–07–06), whenever the fuel 

balance transfer system (FBTS) is used 

during maintenance, prior to further flight, 

perform an inspection to verify that the 

position indicator of the FBTV is in the 

closed position, in accordance with Fokker 

Service Bulletin SBF100–28–030, Revision 1, 

dated December 5, 1994. The inspection 

requirements of this paragraph must be 

accomplished until the deactivation required 

by paragraph (h)(2) of this AD is 

accomplished. 

(i) If the position indicator is in the closed 

position, no further action is required by this 

paragraph. 

(ii) If the position indicator is in the open 

position, close the FBTV, in accordance with 

the Accomplishment Instructions of Fokker 

Service Bulletin SBF100–28–030, Revision 1, 

dated December 5, 1994. 

(2) Within 90 days after April 29, 1996 (the 

effective date of AD 96–07–06, Amendment 

39–9555 (61 FR 14014, March 29, 1996)), 

deactivate the FBTS in accordance with 

either Part 2 or Part 3, as applicable, of the 

Accomplishment Instructions of Fokker 

Service Bulletin SBF100–28–030, Revision 1, 

dated December 5, 1994. Accomplishment of 

the deactivation constitutes terminating 

action for the repetitive inspection 

requirements of paragraph (h)(1) of this AD. 

(i) New Requirements of This AD 

Within 12 months after the effective date 

of this AD, modify the airplane by installing 

an FBTV locking device, in accordance with 

the Accomplishment Instructions of Fokker 

Service Bulletin SBF100–28–066, dated June 

30, 2011, which includes the attachments 

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59728 Federal Register / Vol. 77, No. 190 / Monday, October 1, 2012 / Rules and Regulations 

identified in paragraphs (i)(1) through (i)(5) 

of this AD (* the issue date is not specified 

on the drawing.) 

(1) Fokker Manual Change Notification— 

Maintenance Documentation MCNM–F100– 

145, dated June 30, 2011. 

(2) Fokker Manual Change Notification— 

Operational Documentation MCNO–F100– 

059, dated June 30, 2011. 

(3) Fokker Drawing W41190, Sheet 013, 

Issue P*. 

(4) Fokker Drawing W41190, Sheet 014, 

Issue P*. 

(5) Fokker Drawing W41190, Sheet 016, 

Issue P*. 

(j) Prohibited Modification 

As of the effective date of this AD, no 

person may modify any airplane using 

Fokker Service Bulletin SBF100–28–021, 

dated September 6, 1991 (specified in 

European Aviation Safety Agency (EASA) AD 

2011–0158, dated August 26, 2011, and is not 

incorporated by reference in this AD). That 

service bulletin was cancelled by Fokker 

Service Bulletin SBF100–28–021, Revision 1, 

dated June 30, 2011 (not incorporated by 

reference in this AD). 

(k) Other FAA AD Provisions 

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. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Tom Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone (425) 227–1137; fax (425) 227– 

1149. Information may be emailed to: 9– 

ANM–116–AMOC–REQUESTS@faa.gov. 

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/ 

certificate holding 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. 

(l) Related Information 

Refer to MCAI EASA Airworthiness 

Directive 2011–0158, dated August 26, 2011, 

and the service information specified in 

paragraphs (l)(1), (l)(2), and (l)(3) of this AD, 

for related information. 

(1) Fokker Service Bulletin SBF100–28– 

029, Revision 1, dated November 30, 1993. 

(2) Fokker Service Bulletin SBF100–28– 

030, Revision 1, dated December 5, 1994. 

(3) Fokker Service Bulletin SBF100–28– 

066, dated June 30, 2011, which includes the 

attachments identified in paragraphs (l)(3)(i) 

through (l)(3)(v) of this AD (* the issue date 

is not specified on the drawing). 

(i) Fokker Manual Change Notification— 

Maintenance Documentation MCNM–F100– 

145, dated June 30, 2011. 

(ii) Fokker Manual Change Notification— 

Operational Documentation MCNO–F100– 

059, dated June 30, 2011. 

(iii) Fokker Drawing W41190, Sheet 013, 

Issue P*. 

(iv) Fokker Drawing W41190, Sheet 014, 

Issue P*. 

(v) Fokker Drawing W41190, Sheet 016, 

Issue P*. 

(m) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

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

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(3) The following service information was 

approved for IBR on November 5, 2012. 

(i) Fokker Service Bulletin SBF100–28– 

066, dated June 30, 2011, which includes the 

attachments identified in paragraphs 

(m)(3)(i)(A) through (m)(3)(i)(E) of this AD (* 

the issue date is not specified on the 

drawing). 

(A) Fokker Manual Change Notification— 

Maintenance Documentation MCNM–F100– 

145, dated June 30, 2011. 

(B) Fokker Manual Change Notification— 

Operational Documentation MCNO–F100– 

059, dated June 30, 2011. 

(C) Fokker Drawing W41190, Sheet 013, 

Issue P*. 

(D) Fokker Drawing W41190, Sheet 014, 

Issue P*. 

(E) Fokker Drawing W41190, Sheet 016, 

Issue P*. 

(ii) Reserved. 

(4) The following service information was 

approved for IBR on April 29, 1996 (61 FR 

14014, March 29, 1996). 

(i) Fokker Service Bulletin SBF100–28– 

030, Revision 1, dated December 5, 1994. 

(Pages 1 through 3, 5, 8, and 10 of this 

document are identified as Revision 1, dated 

December 5, 1994. Pages 4, 6, 7, and 9 of this 

document are dated August 28, 1994 (original 

issue).) 

(ii) Reserved. 

(5) The following service information was 

approved for IBR on August 10, 1994 (59 FR 

35237, July 11, 1994). 

(i) Fokker Service Bulletin SBF100–28– 

029, Revision 1, dated November 30, 1993. 

(Pages 1 through 3 of this document are 

identified as Revision 1, dated November 30, 

1993. Pages 4 through 7 of this document are 

dated November 10, 1993 (original issue).) 

(ii) Reserved. 

(6) For 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; email 

technicalservices.fokkerservices@stork.com; 

Internet http://www.myfokkerfleet.com. 

(7) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., Renton, 

WA. For information on the availability of 

this material at the FAA, call 425–227–1221. 

(8) You may view this 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/cfr/ibrlocations.html. 

Issued in Renton, Washington, on 

September 11, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–23052 Filed 9–28–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0327; Directorate 

Identifier 2011–NM–125–AD; Amendment 

39–17198; AD 2012–19–03] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

certain The Boeing Company Model 

DC–10–10, DC–10–10F, DC–10–15, DC– 

10–30, DC–10–30F (KC–10A and KDC– 

10), DC–10–40, DC–10–40F, MD–10– 

10F, and MD–10–30F airplanes. That 

AD currently requires installing or 

replacing with improved parts, as 

applicable, the bonding straps between 

the metallic frame of the fillet and the 

wing leading edge ribs, on both the left 

and right sides of the airplane; and for 

certain airplanes, repositioning or 

replacing two bonding straps, doing a 

bonding-resistance check and an 

inspection to determine correct 

installation of certain bonding straps, 

and applicable corrective actions. This 

new AD adds airplanes to the 

applicability and, depending on the 

airplane configuration, requires 

installing new braided bonding straps, 

inspecting to determine if a certain strap 

is installed and replacing with or 

installing a braided bonding strap if 

necessary, measuring the electrical 

resistance of the bonding straps, 

verifying that brackets have an 

acceptable fillet seal, and doing 

corrective actions if necessary. This AD 

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