Federal Register / Vol. 76, No. 239 / Tuesday, December 13, 2011 / Rules and Regulations 77371 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave. SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

(i) Related Information 

Refer to MCAI European Aviation Safety 

Agency (EASA) AD No.: 2011–0132, dated 

July 12, 2011; Piaggio Aero Industries S.p.A. 

Service Bulletin No. 80–0223, Revision 1, 

dated July 31, 2009; Piaggio Aero Industries 

S.p.A. Mandatory Service Bulletin No. 80– 

0289, dated November 11, 2010; and Piaggio 

Aero Industries S.p.A. Mandatory Service 

Bulletin No. 80–0289, Revision 1, dated 

January 11, 2011, for related information. 

(j) Material Incorporated by Reference 

(1) You must use the following service 

information to do the actions required by this 

AD, unless the AD specifies otherwise. The 

Director of the Federal Register approved the 

incorporation by reference (IBR) under 5 

U.S.C. 552(a) and 1 CFR part 51 of the 

following service information on January 17, 

2012: 

(i) Piaggio Aero Industries S.p.A. Service 

Bulletin No. 80–0223, Revision 1, dated July 

31, 2009; 

(ii) Piaggio Aero Industries S.p.A. 

Mandatory Service Bulletin No. 80–0289, 

dated November 11, 2010; and 

(iii) Piaggio Aero Industries S.p.A. 

Mandatory Service Bulletin No. 80–0289, 

Revision 1, dated January 11, 2011. 

(2) For service information identified in 

this AD, contact Piaggio Aero Industries 

S.p.A–Airworthiness Office, Via Luigi 

Cibrario, 4–16154 Genova-Italy; phone: +39 

010 6481353; fax: +39 010 6481881; email: 

airworthiness@piaggioaero.it; Internet: http:// 

www.piaggioaero.com/#/en/after-sales/

service-support. 

(3) You may review copies of the service 

information at the FAA, Small Airplane 

Directorate, 901 Locust, Kansas City, 

Missouri 64106. For information on the 

availability of this material at the FAA, call 

(816) 329–4148. 

(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 an NARA facility, call (202) 741– 

6030, or go to http://www.archives.gov/ 

federal_register/code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Kansas City, Missouri, on 

December 2, 2011. 

John Colomy, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–31623 Filed 12–12–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0382; Directorate 

Identifier 2010–NM–063–AD; Amendment 

39–16887; AD 2011–25–11] 

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 

all The Boeing Company 757–200, 757– 

200PF, 757–200CB, 757–300, 767–200, 

767–300, and 767–300F series airplanes. 

That AD currently requires revising the 

Limitations section of the airplane flight 

manual (AFM) to advise the flightcrew 

of procedures to follow to ensure that a 

fuel filter impending bypass condition 

due to gross fuel contamination is 

detected in a timely manner. This new 

AD requires installing new operating 

program software (OPS) (Version 7) of 

the engine indication and crew alerting 

system (EICAS) in the EICAS 

computers. This AD also requires 

various concurrent actions. This AD 

also retains the existing AD provision 

that relieves certain airplanes (those 

equipped with certain EICAS OPS 

versions) from the requirements. 

Accomplishment of the new actions 

terminates the requirements of the 

existing AD. This AD was prompted by 

an error in the EICAS OPS. The error 

prevents the display of an advisory 

message to the flightcrew of a left engine 

fuel filter contamination and imminent 

bypass condition, which may indicate 

an imminent multiple engine thrust loss 

or engine malfunction event due to fuel 

contamination. We are issuing this AD 

to correct the unsafe condition on these 

products. 

DATES: This AD is effective January 17, 

2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of January 17, 2012. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, Washington 98124– 

2207; telephone (206) 544–5000, 

extension 1; fax (206) 766–5680; email 

me.boecom@boeing.com; Internet 

https://www.myboeingfleet.com. You 

may review copies of the referenced 

service information at the FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, Washington. 

For information on the availability of 

this material at the FAA, call (425) 227– 

1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: (800) 647–5527) 

is Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Rebel Nichols, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, 

Seattle Aircraft Certification Office 

(ACO), 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 917–6509; fax (425) 917–6590; 

email: rebel.nichols@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2008–09–07, 

Amendment 39–15488 (73 FR 21811, 

April 23, 2008). That AD applies to the 

specified products. The NPRM was 

published in the Federal Register on 

April 20, 2011 (76 FR 22059). That 

NPRM proposed to require installing 

new EICAS OPS (Version 7) in the 

EICAS computers. That NPRM also 

proposed to require various concurrent 

actions, depending on the airplane 

configuration, including installing a 

certain EICAS OPS version, making 

wiring changes, replacing the audio 

accessory unit, replacing certain 

handsets and EICAS computers, 

changing EICAS computer connector 

keying, and loading operational program 

configuration (OPC) software. That 

NPRM also proposed to retain the 

existing AD provision that relieves 

certain airplanes (those equipped with 

certain EICAS OPS versions) from the 

proposed requirements. That NPRM also 

specified that accomplishment of the 

new proposed actions would terminate 

the requirements of the existing AD. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 


jlentini on DSK4TPTVN1PROD with RULES
77372 Federal Register / Vol. 76, No. 239 / Tuesday, December 13, 2011 / Rules and Regulations 

received on the proposal and the FAA’s 

response to each comment. 

Support for NPRM 

Boeing and Air Line Pilots 

Association, International, support the 

intent and contents of the NPRM (76 FR 

22059, April 20, 2011). 

Request To Remove Requirement To 

Install OPS Version 2 

ABX Air requested that we revise the 

NPRM (76 FR 22059, April 20, 2011) to 

remove the requirement to install OPS 

Version 2 before installing OPS Version 

7. ABX Air contended that OPS Version 

2 is not a prerequisite to OPS Version 

7, and does not need to be required in 

the AD. 

We agree with the request, for the 

reasons provided by the commenter. 

Where paragraph (j)(12) of the proposed 

AD would have required installing 

‘‘EICAS OPS Version 2 and EICAS OPC 

software, as applicable,’’ we have 

limited that requirement in this final 

rule to installing ‘‘EICAS OPC software, 

as applicable.’’ 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

with the change described previously. 

We also determined that this change 

will not increase the economic burden 

on any operator or increase the scope of 

the AD. 

Costs of Compliance 

We estimate that this AD affects 1,078 

airplanes of U.S. registry. We estimate 

the costs to comply with the following 

requirements: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

AFM revision (retained from AD 2008–09–07, Amendment 

39–15488 (73 FR 21811, April 23 2008).

1 work-hour × $85 per hour = 

$85.

0 85 $91,630 

EICAS OPS installation (new proposed action) ...................... 1 work-hour × $85 per hour = 

$85.

0 85 91,630 

We have no definitive data for the 

number of U.S.-registered airplanes 

subject to the proposed concurrent 

requirements in this AD, but we provide 

the following estimated per-airplane 

costs to comply with the concurrent 

actions. 

ESTIMATED COSTS FOR CONCURRENT ACTIONS

Action Labor cost Parts cost Cost per 

product 

EICAS OPS installation ......................................... 1–2 work-hours × $85 per hour = $85–$170 ............... Negligible .............. $85–$170 

Wiring change ....................................................... 5 work-hours × $85 per hour = $425 ........................... $501 ...................... 926 

AAU/handset replacement .................................... 1 work-hour × $85 per hour = $85 ............................... Negligible .............. 85 

EICAS computer replacement, wiring change, 

OPC installation.

5–24 work-hours × $85 per hour = $425–$2,040 ........ Negligible .............. 425–2,040 

EICAS OPC installation ........................................ 1 work-hour × $85 per hour = $85 ............................... Negligible .............. 85 

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), 

(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. 

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) 

2008–09–07, Amendment 39–15488 (73 

FR 21811, April 23, 2008), and adding 

the following new AD: 


jlentini on DSK4TPTVN1PROD with RULES
Federal Register / Vol. 76, No. 239 / Tuesday, December 13, 2011 / Rules and Regulations 77373 

2011–25–11 The Boeing Company: 

Amendment 39–16887; Docket No. 

FAA–2011–0382; Directorate Identifier 

2010–NM–063–AD. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective January 17, 2012. 

(b) Affected ADs 

This AD supersedes AD 2008–09–07, 

Amendment 39–15488 (73 FR 21811, April 

23, 2008). 

(c) Applicability 

This AD applies to all The Boeing 

Company 757–200, 757–200PF, 757–200CB, 

757–300, 767–200, 767–300, and 767–300F 

series airplanes; certificated in any category. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 31: Instruments. 

(e) Unsafe Condition 

This AD was prompted by an error in the 

operating program software (OPS) of the 

engine indication and crew alerting system 

(EICAS). The error prevents the display of an 

advisory message to the flightcrew of a left 

engine fuel filter contamination and 

imminent bypass condition, which may 

indicate an imminent multiple engine thrust 

loss or engine malfunction event due to fuel 

contamination. We are issuing this AD to 

prevent malfunction and thrust loss on both 

engines, which could result in a forced offairport landing. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

Restatement of Requirements of AD 2008– 

09–07, Amendment 39–15488 (73 FR 21811, 

April 23, 2008), With No Changes 

(g) Revision of Airplane Flight Manual 

(AFM) 

Except as provided by paragraphs (h) and 

(i) of this AD: Within 30 days after May 8, 

2008 (the effective date of AD 2008–09–07, 

Amendment 39–15488 (73 FR 21811, April 

23, 2008)), revise the Limitations section of 

the applicable AFM to include the following. 

This may be done by inserting a copy of this 

AD into the AFM. 

‘‘If the STATUS cue shows while on the 

ground after engine start or during flight, 

select the status page on the secondary 

EICAS display, and verify the ‘‘L ENG FUEL 

FILT’’ message is not shown. If the ‘‘L ENG 

FUEL FILT’’ message is not shown on the 

status page, the secondary engine parameters 

may be reselected on the secondary EICAS 

display, or the display may be blanked. If the 

‘‘L ENG FUEL FILT’’ message is shown on 

the status display, accomplish the ENGINE 

FUEL FILTER non-normal checklist as 

published in the Boeing Quick Reference 

Handbook. If on the ground, check the 

Dispatch Deviations Guide (DDG), or operator 

equivalent. 

In the event that the status level ‘‘L ENG 

FUEL FILT’’ and advisory level ‘‘R ENG 

FUEL FILT’’ messages are simultaneously 

shown, an impending fuel filter bypass 

condition exists on both engines. With both 

messages shown, airplane fuel system 

contamination may be present and may result 

in erratic engine operation or flameout. 

Further flight crew action in response to 

either or both the ‘‘L ENG FUEL FILT’’ statuslevel message and the ‘‘R ENG FUEL FILT’’ 

advisory level messages being shown are not 

established by Boeing or the FAA. Any 

further flight crew action should be 

determined by individual operator policy. 

Boeing policy on flight crew use of statuslevel messages has not changed. After engine 

start, any condition having an adverse effect 

on safe continuation of the flight appears as 

an EICAS alert message (Warning, Caution, or 

Advisory). If other status-level messages are 

shown as a consequence of complying with 

these temporary operating instructions, the 

flight crew should respond in accordance 

with the appropriate operator policy. 

Dispatch of the airplane with an inoperative 

EICAS display unit is prohibited.’’ 

(h) Exception to AFM Limitations 

Requirement 

If all affected airplanes in an operator’s 

fleet have been verified by the operator to 

have EICAS computer part number 

S242N701–1001 and only EICAS OPS 

versions other than Version 6 software that 

are FAA approved for that airplane, then 

accomplishment of the actions specified in 

paragraph (g) of this AD is not required. 

New Requirements of This AD 

(i) EICAS OPS Installation 

Except as provided by paragraph (k) of this 

AD: Within 90 days after the effective date 

of this AD, install EICAS OPS Version 7 in 

the left and right EICAS computers, in 

accordance with the applicable service 

information specified in paragraph (i)(1) or 

(i)(2) of this AD. Accomplishment of the 

applicable requirements of paragraphs (i) and 

(j) of this AD terminates the requirements of 

paragraph (g) of this AD, provided that those 

actions have been accomplished on all 

airplanes operated within an operator’s fleet. 

(1) For Model 757 airplanes: Use Boeing 

Special Attention Service Bulletin 757–31– 

0192, dated September 11, 2009. 

(2) For Model 767–200, –300, and –300F 

series airplanes: Use Boeing Special 

Attention Service Bulletin 767–31–0267, 

dated September 11, 2009. 

(j) Concurrent Requirements 

For airplanes subject to the requirements of 

paragraph (i) of this AD: Before or 

concurrently with accomplishment of the 

requirements of paragraph (i) of this AD, do 

the applicable actions specified in 

paragraphs (j)(1) through (j)(12) of this AD. 

(1) For Model 757–200, 757–200CB, 757– 

200PF series airplanes, as identified in 

Boeing Service Bulletin 757–31–0104, dated 

December 5, 2002: Install EICAS OPS Version 

5, in accordance with Boeing Service Bulletin 

757–31–0104, dated December 5, 2002. 

(2) For Model 757–300 series airplanes, as 

identified in Boeing Service Bulletin 757–31– 

0105, dated December 5, 2002: Install EICAS 

OPS Version 5, in accordance with Boeing 

Service Bulletin 757–31–0105, dated 

December 5, 2002. 

(3) For Model 767–200 and –300 airplanes, 

as identified in Boeing Service Bulletin 767– 

23–0159, Revision 2, dated January 11, 2007: 

Change wires from the audio accessory unit 

(AAU) on the E2–5 shelf to the bell chime 

module in the warning electronics unit 

(WEU) (P51), in accordance with Boeing 

Service Bulletin 767–23–0159, Revision 2, 

dated January 11, 2007. 

(4) For Model 767–300 series airplanes, as 

identified in Boeing Special Attention 

Service Bulletin 767–23–0160, dated May 31, 

2001: Replace the AAU with a new or 

serviceable unit, in accordance with Boeing 

Special Attention Service Bulletin 767–23– 

0160, dated May 31, 2001. 

(5) For Model 767–300 series airplanes, as 

identified in Boeing Service Bulletin 767–23– 

0167, dated February 28, 2002: Replace the 

AAU with a new or serviceable unit, in 

accordance with Boeing Service Bulletin 

767–23–0167, dated February 28, 2002. 

(6) For Model 767–200 and 767–300 series 

airplanes, as identified in Boeing Service 

Bulletin 767–23–0164, dated May 31, 2001: 

Replace the pilots’ handset on the P8 panel, 

replace 5 attendant handsets, and replace the 

AAU on the E2–5 shelf in the main 

equipment center, as applicable; in 

accordance with Boeing Service Bulletin 

767–23–0164, dated May 31, 2001. 

(7) For Model 767–200, 767–300, and 767– 

300F series airplanes, as identified in Boeing 

Service Bulletin 767–31–0091, Revision 4, 

dated July 7, 2005: Replace the left and right 

EICAS computers in the E8 rack, make wire 

changes in the E8 shelf, change the left and 

right EICAS computer connector keying on 

the E8 shelf, and load operational program 

configuration (OPC) software into both left 

and right EICAS computers; in accordance 

with Boeing Service Bulletin 767–31–0091, 

Revision 4, dated July 7, 2005. These actions 

are also required by AD 2004–10–05, 

Amendment 39–13635 (69 FR 28051, May 18, 

2004). 

(8) For Model 767–200 and 767–300 series 

airplanes, as identified in Boeing Service 

Bulletin 767–31–0098, including Appendixes 

A, B, and C, Revision 2, dated October 21, 

1999: Replace the left and right EICAS 

computers in the E8 rack, make wire changes 

in the E8 shelf, change the left and right 

EICAS computer connector keying on the E8 

shelf, and load OPC software into both left 

and right EICAS computers; in accordance 

with Boeing Service Bulletin 767–31–0098, 

including Appendixes A, B, and C, Revision 

2, dated October 21, 1999. These actions are 

also required by AD 2004–10–05 (69 FR 

28051, May 18, 2004). 

(9) For Model 767–300 series airplanes, as 

identified in Boeing Service Bulletin 767–31– 

0099, including Appendixes A, B, and C, 

Revision 3, dated February 8, 2001: Replace 

the left and right EICAS computers in the E8 

rack, make wire changes in the E8 shelf, 

change the left and right EICAS computer 

connector keying on the E8 shelf, and load 

OPC software into both left and right EICAS 

computers; in accordance with Boeing 

Service Bulletin 767–31–0099, including 

Appendixes A, B, and C, Revision 3, dated 

February 8, 2001. These actions are also 


jlentini on DSK4TPTVN1PROD with RULES
77374 Federal Register / Vol. 76, No. 239 / Tuesday, December 13, 2011 / Rules and Regulations 

required by AD 2004–10–05 (69 FR 28051, 

May 18, 2004). 

(10) For Model 767–200 and 767–300 

series airplanes, as identified in Boeing 

Service Bulletin 767–31–0100, including 

Appendixes A, B, and C, Revision 2, dated 

July 29, 1999: Replace the left and right 

EICAS computers in the E8 rack, make wire 

changes in the E8 shelf, change the left and 

right EICAS computer connector keying on 

the E8 shelf, and load OPC software into both 

left and right EICAS computers; in 

accordance with Boeing Service Bulletin 

767–31–0100, including Appendixes A, B, 

and C, Revision 2, dated July 29, 1999. These 

actions are also required by AD 2004–10–05 

(69 FR 28051, May 18, 2004). 

(11) For Model 767–200 and 767–300 

series airplanes, as identified in Boeing 

Service Bulletin 767–31–0101, including 

Appendixes A, B, and C, dated July 6, 2000: 

Replace the left and right EICAS computers 

in the E8 rack, make wire changes in the E8 

shelf, change the left and right EICAS 

computer connector keying on the E8 shelf, 

and load OPC software into both left and 

right EICAS computers; in accordance with 

Boeing Service Bulletin 767–31–0101, 

including Appendixes A, B, and C, dated July 

6, 2000. These actions are also required by 

AD 2004–10–05 (69 FR 28051, May 18, 2004). 

(12) For Model 767–200, 767–300, and 

767–300F series airplanes, as identified in 

the table in paragraph 3.D. of Boeing Service 

Bulletin 767–31–0114, Revision 1, dated June 

8, 2000: Install EICAS OPC software, as 

applicable, in accordance with Boeing 

Service Bulletin 767–31–0114, Revision 1, 

dated June 8, 2000. 

(k) Exception to OPS Installation 

Requirement 

For any airplane verified by the operator to 

have EICAS computer part number 

S242N701–1001 and only EICAS OPS 

versions other than Version 6 software that 

are FAA approved for that airplane, the 

actions specified in paragraphs (i) and (j) of 

this AD are not required. 

(l) Parts Installation 

As of the effective date of this AD, no 

person may install EICAS OPS Version 6 

software on any airplane. 

(m) Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

Accomplishment before the effective date 

of this AD of the actions specified in a 

service bulletin identified in table 1 of this 

AD is acceptable for compliance with the 

applicable requirements of paragraph (j) of 

this AD, except as noted. 

TABLE 1—CREDIT SERVICE BULLETINS

Boeing Service Bulletin— Revision— Dated— Airplanes excluded from compliance approval— 

767–23–0159 ............................ 1 December 5, 2002 ................... No exceptions. 

767–31–0091 ............................ 1 February 4, 1999 ..................... Acceptable except for airplanes VN634, VN635, VH171, 

VN172, VF251, and VN198. 

767–31–0091 ............................ 2 February 24, 2000 ................... Acceptable except for airplane VN198. 

767–31–0091 ............................ 3 April 27, 2000 .......................... No exceptions. 

767–31–0098 ............................ .................... August 27, 1998 ...................... Acceptable except for airplanes VB051 through VB054, 

VN307 through VN314, VN676, and VK046 through VK054. 

767–31–0098 ............................ 1 February 4, 1999 ..................... Acceptable except for airplanes VB051 through VB054, 

VN307 through VN314, VN676, and VK046 through VK054. 

767–31–0099 ............................ .................... August 6, 1998 ........................ Acceptable only for airplanes VL871 through VL873. 

767–31–0099 ............................ 1 February 4, 1999 ..................... Acceptable only for airplanes VL871 through VL873. 

767–31–0099 ............................ 2 June 17, 1999 .......................... Acceptable only for airplanes VL871 through VL873. 

767–31–0100 ............................ .................... August 20, 1998 ...................... No exceptions. 

767–31–0100 ............................ 1 February 4, 1999 ..................... No exceptions. 

767–31–0114 ............................ .................... March 18, 1999 ....................... Acceptable except for airplanes VL891 through VL910, VR201 

through VR206, and VW701 through VW721. 

(n) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. 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 manager of the ACO, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

Information may be emailed to 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. 

(2) 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. 

(o) Related Information 

For more information about this AD, 

contact Rebel Nichols, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; telephone (425) 917–6509; fax (425) 

917–6590; email: rebel.nichols@faa.gov. 

(p) Material Incorporated by Reference 

(1) You must use the following service 

information to do the actions required by this 

AD, unless the AD specifies otherwise. The 

Director of the Federal Register approved the 

incorporation by reference (IBR) under 5 

U.S.C. 552(a) and 1 CFR part 51 of the 

following service information on the date 

specified: 

(i) Boeing Special Attention Service 

Bulletin 757–31–0192, dated September 11, 

2009, approved for IBR January 17, 2012. 

(ii) Boeing Special Attention Service 

Bulletin 767–31–0267, dated September 11, 

2009, approved for IBR January 17, 2012. 

(iii) Boeing Service Bulletin 757–31–0104, 

dated December 5, 2002, approved for IBR 

January 17, 2012. 

(iv) Boeing Service Bulletin 757–31–0105, 

dated December 5, 2002, approved for IBR 

January 17, 2012. 

(v) Boeing Service Bulletin 767–23–0159, 

Revision 2, dated January 11, 2007, approved 

for IBR January 17, 2012. 

(vi) Boeing Special Attention Service 

Bulletin 767–23–0160, dated May 31, 2001, 

approved for IBR January 17, 2012. 

(vii) Boeing Service Bulletin 767–23–0164, 

dated May 31, 2001, approved for IBR 

January 17, 2012. 

(viii) Boeing Service Bulletin 767–23–0167, 

dated February 28, 2002, approved for IBR 

January 17, 2012. 

(ix) Boeing Service Bulletin 767–31–0091, 

Revision 4, dated July 7, 2005, approved for 

IBR January 17, 2012. 

(x) Boeing Service Bulletin 767–31–0098, 

including Appendixes A, B, and C, Revision 

2, dated October 21, 1999, approved for IBR 

January 17, 2012. 

(xi) Boeing Service Bulletin 767–31–0099, 

including Appendixes A, B, and C, Revision 

3, dated February 8, 2001, approved for IBR 

January 17, 2012. 

(xii) Boeing Service Bulletin 767–31–0100, 

including Appendixes A, B, and C, Revision 

2, dated July 29, 1999, approved for IBR 

January 17, 2012. 

(xiii) Boeing Service Bulletin 767–31–0101, 

including Appendixes A, B, and C, dated July 

6, 2000, approved for IBR January 17, 2012. 

(xiv) Boeing Service Bulletin 767–31–0114, 

Revision 1, dated June 8, 2000, approved for 

IBR January 17, 2012. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, Washington 98124–2207; telephone 

(206) 544–5000, extension 1; fax (206) 766– 


jlentini on DSK4TPTVN1PROD with RULES
Federal Register / Vol. 76, No. 239 / Tuesday, December 13, 2011 / Rules and Regulations 77375 

5680; email me.boecom@boeing.com; Internet 

https://www.myboeingfleet.com. 

(3) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

(425) 227–1221. 

(4) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at an NARA facility, 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 

November 29, 2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–31418 Filed 12–12–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1190; Directorate 

Identifier 2010–SW–038–AD; Amendment 

39–16877; AD 2011–25–01] 

RIN 2120–AA64 

Airworthiness Directives; Apical 

Industries, Inc., (Apical) Emergency 

Float Kits 

AGENCY: Federal Aviation 

Administration, DOT. 

ACTION: Final rule. 

SUMMARY: This amendment adopts a 

new airworthiness directive (AD) for the 

Apical emergency float kits installed on 

certain model helicopters under 

supplemental type certificates. This AD 

requires adding placards on each side of 

the fuselage to identify the location and 

operation of the liferaft external 

inflation handle. This AD also requires 

replacing each liferaft operation placard 

to state that external liferafts are 

installed. This amendment is prompted 

by a report of a helicopter that crashed 

into the water, and the pilot did not 

deploy the floats and liferafts. Two 

external T-handles were available for 

deployment of the liferafts but were not 

used by the passengers because they 

were unaware of their location. The 

actions specified by this AD are 

intended to prevent helicopter 

occupants from further injury due to 

unnecessary exposure to harsh water 

conditions and to aid in deploying 

liferafts when liferafts are available on 

the helicopter and can be activated after 

a water landing. 

DATES: Effective January 17, 2012. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of January 17, 

2012. 

ADDRESSES: You may get the service 

information identified in this AD from 

Apical Industries, Inc., 2608 Temple 

Heights Drive, Oceanside, California 

92056–3512, telephone (760) 724–5300, 

fax (760) 758–9612, http:// 

www.apicalindustries.com/. 

Examining the Docket: You may 

examine the docket that contains this 

AD, any comments, and other 

information on the Internet at http:// 

www.regulations.gov or at the Docket 

Operations office, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC. 

FOR FURTHER INFORMATION CONTACT: 

Venessa Stiger, Aviation Safety 

Engineer, FAA, Los Angeles Aircraft 

Certification Office, 3960 Paramount 

Blvd., Lakewood, California 90712– 

4137, telephone (562) 627–5337, fax 

(562) 627–5210. 

SUPPLEMENTARY INFORMATION: A 

proposal to amend 14 CFR part 39 to 

include an AD for helicopters modified 

in accordance with certain 

supplemental type certificates with 

certain emergency float kits, was 

published in the Federal Register on 

December 7, 2010 (75 FR 75934). That 

action proposed to require, for certain 

model helicopters modified per 

Supplemental Type Certificate Number 

SR01535LA, SR01779LA, SR01813LA, 

SR01855LA, or SR00856LA, adding an 

external placard near the external THandles to provide instructions for the 

operation of the liferaft external 

inflation handle. That action also 

proposed to require replacing earlier 

installed liferaft operation placards with 

more recent placards. 

We provided the public the 

opportunity to participate in developing 

this AD. We received no comments on 

the proposal or on the determination of 

the cost to the public. 

We estimate that this AD will affect 

324 helicopters of U.S. registry, and it 

will take about 1⁄2 work hour per 

helicopter to install 4 or 6 placards at 

an average labor rate of $85 per work 

hour. Required parts will cost about $70 

per helicopter. Based on these figures, 

we estimate the total cost impact of this 

AD on U.S. operators is $36,450 for the 

entire fleet. 

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); 

3. Will not affect intrastate aviation in 

Alaska to the extent that it justifies 

making a regulatory distinction; 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 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 AD. 

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 Federal Aviation Administration 

amends part 39 of the Federal Aviation 

Regulations (14 CFR part 39) as follows: 


jlentini on DSK4TPTVN1PROD with RULES