Federal Register / Vol. 76, No. 166 / Friday, August 26, 2011 / Rules and Regulations 53317 

obtained from American Eurocopter 

Corporation, 2701 Forum Drive, Grand 

Prairie, TX 75053–4005, telephone (800) 

232–0323, fax (972) 641–3710, or at http:// 

www.eurocopter.com. Copies may be 

inspected at the FAA, Office of the Regional 

Counsel, Southwest Region, 2601 Meacham 

Blvd., Room 663, Fort Worth, Texas, or at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http:// 

www.archives.gov/federal_register/ 

code_of_federal_regulations/ 

ibr_locations.html. 

(f) This amendment becomes effective on 

September 12, 2011. 

Note: The subject of this AD is addressed 

in European Aviation Safety Agency (France) 

Emergency AD No. 2009–0109–E, dated May 

7, 2009. 

Issued in Fort Worth, Texas, on July 21, 

2011. 

Kim Smith, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 2011–21477 Filed 8–25–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–28661; Directorate 

Identifier 2007–NM–013–AD; Amendment 

39–16785; AD 2011–18–03] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 737–600, –700, –700C, 

–800, and –900 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD requires 

installation of an automatic shutoff 

system for the center tank fuel boost 

pumps, and installation of a placard in 

the airplane flight deck if necessary. 

This AD also requires revisions to the 

Limitations and Normal Procedures 

sections of the airplane flight manual to 

advise the flightcrew of certain 

operating restrictions for airplanes 

equipped with an automated center tank 

fuel pump shutoff control. This AD 

further requires installation of a 

secondary control relay for the electrical 

control circuit of each of the two center 

tank fuel boost pumps. Additionally, 

this AD requires a revision to the 

maintenance program to incorporate 

Airworthiness Limitation (AWL) No. 

28–AWL–23. This AD also provides an 

option of installation and maintenance 

of universal fault interrupters using a 

certain supplemental type certificate, 

which terminates certain requirements 

of this AD. This AD was prompted by 

fuel system reviews conducted by the 

manufacturer. We are issuing this AD to 

prevent center tank fuel pump operation 

with continuous low pressure, which 

could lead to friction sparks or 

overheating in the fuel pump inlet that 

could create a potential ignition source 

inside the center fuel tank. These 

conditions, in combination with 

flammable fuel vapors, could result in a 

center fuel tank explosion and 

consequent loss of the airplane. 

DATES: This AD is effective September 

30, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of September 30, 2011. 

ADDRESSES: For Boeing 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; e-mail 

me.boecom@boeing.com; Internet 

https://www.myboeingfleet.com. For 

TDG Aerospace information identified 

in this AD, contact TDG Aerospace, Inc., 

545 Corporate Drive, Escondido, 

California 92029; telephone 760–466– 

1040; fax 760–466–1038; Internet http:// 

www.tdgaerospace.com; e-mail 

info@tdgaerospace.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: Tak 

Kobayashi, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; phone: (425) 

917–6499; fax: (425) 917–6590; e-mail: 

Takahisa.Kobayashi@faa.gov. 

SUPPLEMENTARY INFORMATION:

Discussion 

We issued a supplemental notice of 

proposed rulemaking (SNPRM) to 

amend 14 CFR part 39 to include an 

airworthiness directive (AD) that would 

apply to the specified products. That 

SNPRM published in the Federal 

Register on March 8, 2011 (76 FR 

12634). The original NPRM (72 FR 

37479, July 10, 2007) proposed to 

require installation of an automatic 

shutoff system for the center tank fuel 

boost pumps, installation of a placard in 

the airplane flight deck if necessary, and 

concurrent modification of the P5–2 fuel 

control module assembly. The original 

NPRM also proposed to require 

revisions to the Limitations and Normal 

Procedures sections of the airplane 

flight manual (AFM) to advise the 

flightcrew of certain operating 

restrictions for airplanes equipped with 

an automated center tank fuel pump 

shutoff control. Additionally, the 

original NPRM proposed to require a 

revision to the Airworthiness 

Limitations (AWL) section of the 

Instructions for Continued 

Airworthiness (ICA) to incorporate AWL 

No. 28–AWL–19 and No. 28–AWL–23. 

The original NPRM further proposed to 

require installation of a secondary 

control relay for the electrical control 

circuit of each of the two center tank 

fuel boost pumps. The SNPRM 

proposed to revise the original NPRM by 

adding airplanes, adding additional 

operational testing of the automatic 

shutoff system for certain airplanes, 

removing the requirement for 

incorporating AWL No. 28–AWL–19 

into the AWL section of the ICA, and 

adding an option of installation and 

maintenance of universal fault 

interrupters using a certain 

supplemental type certificate. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal and the FAA’s 

response to each comment. 

Support for SNPRM 

Delta Airlines (Delta) stated that it has 

no objections to the SNPRM. 

Request To Correct Service Information 

Citation 

Boeing requested that we revise the 

fifth paragraph under the ‘‘Explanation 

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53318 Federal Register / Vol. 76, No. 166 / Friday, August 26, 2011 / Rules and Regulations 

of Additional Changes Made to this 

Supplemental NPRM’’ section of the 

SNPRM to correct the model 

designation portion of the document 

citation provided in that paragraph. 

Although we agree that there was a 

typographical error in the document 

citation specified in the ‘‘Explanation of 

Additional Changes Made to this 

Supplemental NPRM’’ section of the 

SNPRM, we do not agree to revise this 

AD in this regard, as that section is not 

restated in the final rule. No change to 

the AD is necessary in this regard. 

Request To Include Definition in 

Paragraph (b) of the SNPRM 

Boeing requested that we revise 

paragraph (b) of the SNPRM to properly 

define ‘‘2001–08–24’’ as an 

airworthiness directive. We agree and 

have revised paragraph (b) of this AD 

accordingly. 

Request To Revise Conditions Specified 

in Paragraph (h) of the SNPRM 

Boeing requested that we revise 

paragraph (h) of the SNPRM to remove 

the last sentence of the paragraph, 

which specifies the conditions when a 

placard is not necessary. Boeing stated 

that this sentence is confusing and 

possibly contradictory, and that the 

placard requirement provided in those 

paragraphs is well defined without the 

use of this sentence. 

We agree partially. We agree to 

remove the first condition specified in 

the second to last sentence of paragraph 

(h) of this AD, which states, ‘‘If 

automatic shutoff systems are installed 

concurrently on all airplanes in an 

operator’s fleet in accordance with 

paragraph (g) of this AD * * *, the 

placard installation specified in this 

paragraph is not necessary.’’ If the 

automatic shutoff system is 

concurrently installed on all airplanes, 

there will be no airplanes on which a 

placard would be required to be 

installed. Therefore, this condition is 

unnecessary. We have revised paragraph 

(h) of this AD to remove this condition. 

We do not agree to remove the second 

condition in the second to last sentence 

of paragraph (h) of this AD. That 

condition provides an option to 

operators that prefer not to install a 

placard on any airplane in their fleet. If 

an operator intends to maintain fuel 

usage restrictions specified in AD 2002– 

24–51, Amendment 39–12992 (68 FR 

10, January 2, 2003), and AD 2001–08– 

24, Amendment 39–12201 (66 FR 

20733, April 25, 2001), for all airplanes 

in the fleet until the automatic shutoff 

systems are installed on all of those 

airplanes, the operator is not required to 

install a placard, even after installing 

the automatic shutoff system on any 

airplane in its fleet. We have 

determined that this option should 

remain available to operators, and have 

not revised paragraph (h) of this AD to 

remove this condition. We also have not 

revised paragraph (s) of this AD to 

remove the same condition specified in 

the second to last sentence of paragraph 

(h) of this AD. 

Also, we acknowledge that a reference 

to AD 2001–08–24, Amendment 39– 

12201 (66 FR 20733, April 25, 2001), 

was inadvertently omitted in the last 

sentence of paragraph (h) of the SNPRM. 

We have added a reference to AD 2001– 

08–24 in paragraph (h) of this AD, and 

provided additional clarification in the 

‘‘Additional Changes Made to this AD’’ 

section of this AD. 

Request To Revise Proposed Wording of 

Placard in Paragraph (h) of the SNPRM 

Southwest Airlines (Southwest) 

requested that the SNPRM be revised to 

allow alternative wording for the 

placard required by paragraph (h) of the 

SNPRM. Southwest stated that it has a 

placard adjacent to the pilot’s primary 

flight display on all of its airplanes that 

are not equipped with an automatic 

shutoff system, which reads, ‘‘AD 2002– 

19–52 fuel usage restrictions required.’’ 

Southwest reported that it is unable to 

find any language in either AD 2002– 

19–52, Amendment 39–12900 (67 FR 

61253, September 30, 2002), or AD 

2002–24–51, Amendment 39–12992 (68 

FR 10, January 2, 2003), that requires 

the placard text proposed in paragraph 

(h) of the SNPRM. 

We agree partially. We have 

determined that clarification of 

paragraph (h) of this final rule is 

necessary to prevent inadvertent 

removal of the placard required by 

paragraph (h) of this AD and by 

paragraph (e) of AD 2002–19–52, 

Amendment 39–12900 (67 FR 61253, 

September 30, 2002). As discussed in 

the preamble of the SNPRM, AD 2002– 

19–52 requires installation of a placard, 

and provides an optional terminating 

action that allows removal of that 

placard. The intent of the placard 

installation required by AD 2002–19–52 

is to address mixed operation of the 

airplanes with and without the optional 

terminating action accomplished within 

an operator’s fleet. After issuance of AD 

2002–19–52, we issued AD 2002–24–51, 

Amendment 39–12992 (68 FR 10, 

January 2, 2003), to mandate fuel usage 

restrictions identical to those required 

by AD 2002–19–52, to address an unsafe 

condition not related to AD 2002–19– 

52. Airworthiness Directive 2002–24–51 

did not require installation of a placard, 

because terminating action for that AD 

was not available at the time, and, 

therefore, there was no concern about 

mixed fleet operation. 

We do not agree to revise the placard 

wording required by paragraph (h) of 

this AD. However, if a placard that 

refers to AD 2002–19–52, Amendment 

39–12900 (67 FR 61253, September 30, 

2002), already exists on an airplane, we 

have determined that use of that placard 

does meet the placard installation 

requirement of paragraph (h) of this AD. 

Therefore, we have revised paragraph 

(h) of this AD to state that installation 

of a placard in accordance with 

paragraph (e) of AD 2002–19–52 is 

acceptable for compliance with the 

requirements of paragraph (h) of this 

AD, and that the placard may be 

removed from an airplane only once the 

terminating action specified in 

paragraph (g) of AD 2002–19–52 and 

installation of an automatic shutoff 

system required by paragraph (g) of this 

AD have been accomplished. 

Request To Reference Latest AWL 

Revision in Paragraph (k) of the 

SNPRM 

Boeing requested that we revise 

paragraph (k) of the SNPRM to reference 

the latest revision of the maintenance 

planning data (MPD) document. Boeing 

stated that the document specified in 

paragraph (k) of the SNPRM has been 

revised, and that the applicable 

subsection has changed from ‘‘G’’ to 

‘‘E.1.’’ in Revision February 2011. 

We agree that this AD should refer to 

the current revision of the MPD 

document specified in paragraph (k) of 

this AD. Therefore, we have revised 

paragraph (k) of this AD to refer to 

Subsection E, AWLs—Fuel Systems, of 

Section 9, Airworthiness Limitations 

(AWLs) and Certification Maintenance 

Requirements (CMRs), of the Boeing 

737–600/700/800/900 MPD Document, 

D626A001–CMR, Revision March 2011. 

We have also added new paragraph (t) 

to this AD (and re-identified subsequent 

paragraphs accordingly) to give credit to 

operators that accomplish the AWL 

revision required by paragraph (k) of 

this AD before the effective date of this 

AD using any of the following revisions 

of Subsection G, Airworthiness 

Limitations—Fuel System AWLs, of 

Section 9, Airworthiness Limitations 

(AWLs) and Certification Maintenance 

Requirements (CMRs), of the Boeing 

737–600/700/800/900 MPD Document, 

D626A001–CMR: 

• Revision March 2008 

• Revision April 2008 

• Revision June 2008 

• Revision February 2009 

• Revision March 2009 

• Revision August 2009 

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Federal Register / Vol. 76, No. 166 / Friday, August 26, 2011 / Rules and Regulations 53319 

• Revision September 2009 

• Revision November 2009 

• Revision January 2010 

• Revision May 2010 

• Revision July 2010 

• Revision August 2010 

Paragraph (t) of this AD also provides 

credit to operators that accomplish the 

AWL revision required by paragraph (k) 

of this AD before the effective date of 

this AD using Subsection E, AWLs— 

Fuel Systems, of Section 9, 

Airworthiness Limitations (AWLs) and 

Certification Maintenance Requirements 

(CMRs), of the Boeing 737–600/700/800/ 

900 MPD Document, D626A001–CMR, 

Revision February 2011. 

Request To Clarify Terminating Action 

for Paragraphs (m) and (n) of SNPRM 

Delta requested that we revise 

paragraphs (m) and (n) of the SNPRM to 

clarify that accomplishing the actions 

specified in paragraph (s) of the SNPRM 

terminates the actions required in 

paragraphs (m) and (n) of the SNPRM. 

Delta pointed out that paragraph (s) of 

the SNPRM terminates only paragraphs 

(g) through (k) of the SNPRM, and not 

paragraphs (m) and (n) of the SNPRM. 

Delta stated that operators planning to 

comply with the proposed requirements 

by installing universal fault interrupters 

(UFIs) in accordance with paragraph (s) 

of the SNPRM will not accomplish 

paragraphs (g), (h), and (i) of the 

SNPRM. Therefore, Delta asserted that, 

as the SNPRM is currently written, 

operators that do not do the actions 

specified in paragraphs (g), (h), and (i) 

of the SNPRM will not be able to 

comply with the requirements of 

paragraphs (m) and (n) of the SNPRM. 

We agree. Accomplishing the optional 

terminating action specified in 

paragraph (s) of this AD terminates the 

requirements of paragraphs (g) through 

(k) of this AD, making the optional 

terminating action specified in 

paragraph (s) of this AD equivalent to 

the actions required by paragraphs (g) 

through (k) of this AD. Therefore, 

complying with paragraph (s) of this AD 

meets the condition required to 

terminate the requirements of paragraph 

(a) of AD 2001–08–24, Amendment 39– 

12201 (66 FR 20733, April 25, 2001), 

and paragraph (b) of AD 2002–24–51, 

Amendment 39–12992 (68 FR 10, 

January 2, 2003). We have revised 

paragraphs (m) and (n) of this AD to 

state that accomplishing the actions 

(i.e., optional terminating action) 

specified in paragraph (s) of this AD 

terminates the requirements of 

paragraph (a) of AD 2001–08–24 and 

paragraph (b) of AD 2002–24–51. 

Request To Provide Credit for 

Aerospace Supplemental Type 

Certificate (STC) 

Continental Airlines (Continental) 

requested that we revise the SNPRM to 

give credit for incorporating universal 

fault interrupters (UFIs) using TDG 

Aerospace STC ST02076LA before the 

effective date of the AD. Continental 

pointed out that paragraphs (q) and (r) 

of the SNPRM provide credit for actions 

done before the effective date of the AD 

using other service information. 

While we do agree that installing TDG 

Aerospace UFIs before the effective date 

of this AD is acceptable for terminating 

certain actions required by this AD, we 

do not agree to revise the AD to provide 

specific credit for those actions. 

Installing TDG Aerospace UFIs, as 

specified in paragraph (s) of this AD, is 

acceptable both before and after the 

effective date of this AD. Operators are 

always permitted to accomplish the 

requirements of an AD at a time earlier 

than the specified compliance time. We 

have not changed the AD in this regard. 

Request To Revise Paragraph (v) of the 

SNPRM To Add Contact Information 

Delta requested that we revise 

paragraph (v) of the SNPRM to add 

contact information for TDG Aerospace. 

Delta pointed out that contact 

information for the other service 

information identified in the SNPRM is 

provided, but not for TDG Aerospace. 

We agree partially. We do not agree to 

revise paragraph (v) of the SNPRM, 

because that paragraph is not restated in 

this final rule. However, we do agree to 

provide contact information for TDG 

Aerospace. We have revised the 

ADDRESSES section of this AD to include 

this contact information. 

Additional Changes Made to This AD 

We have revised paragraph (h) of this 

AD to clarify when a placard is not 

necessary. We have determined that the 

second to last sentence of paragraph (h) 

of this AD should also refer to AD 2001– 

08–24, Amendment 39–12201 (66 FR 

20733, April 25, 2001), for clarity. 

Operators that choose to maintain the 

fuel usage restrictions of AD 2002–24– 

51, Amendment 39–12992 (68 FR 10, 

January 2, 2003), for all airplanes in 

their fleet do not meet the condition to 

terminate AD 2002–24–51 and AD 

2001–08–24 until the actions required 

by paragraphs (g) and (i) of this AD are 

accomplished on all airplanes in their 

fleet. Therefore, those operators are 

otherwise required to comply with the 

requirements of AD 2001–08–24, 

regardless of whether that AD is 

mentioned in paragraph (h) of this AD. 

Therefore, this change does not increase 

the burden on operators. 

We have revised paragraph (s) of this 

AD to specify that installation of TDG 

Aerospace UFIs, as provided in that 

paragraph, must be done in accordance 

with a method approved by the 

Manager, Seattle Aircraft Certification 

Office (ACO), FAA, because referring to 

the STC now violates Office of the 

Federal Register (OFR) policies for 

approval of optional materials 

‘‘incorporated by reference’’ in rules. 

We have added Note 5 to this AD to 

specify that additional guidance on 

installing TDG Aerospace UFIs can be 

found in TDG Aerospace STC 

ST02076LA. 

We have also revised paragraph (s) of 

this AD to clarify the time limit for 

doing the optional terminating action. 

Since paragraph (s) of this AD 

terminates the actions required by 

paragraphs (g) through (k) of this AD, if 

done, paragraph (s) of this AD must be 

accomplished within the earliest time 

specified among those paragraphs to be 

considered terminating action; that 

earliest time is 36 months. 

Additionally, we have revised 

paragraph (s) of this AD to allow the use 

of alternative placard wording that is 

approved by an appropriate FAA 

Principal Operations Inspector, instead 

of requiring approval of alternative 

placard wording as an alternative 

method of compliance in accordance 

with paragraph (u) of this AD. 

We have also revised paragraph (s) of 

this AD by adding a statement to allow 

installation of a placard in accordance 

with paragraph (e) of AD 2002–19–52, 

Amendment 39–12900 (67 FR 61253, 

September 30, 2002). 

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 changes described previously— 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the SNPRM for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the SNPRM. 

We also determined that these 

changes 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 685 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

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53320 Federal Register / Vol. 76, No. 166 / Friday, August 26, 2011 / Rules and Regulations 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product 

Number of 

U.S.-registered 

airplanes 

Cost on U.S. operators 

Installation of the automatic shutoff system 

(Boeing Alert Service 

Bulletin 737– 

28A1206).

Between 94 and 117 

(depending on airplane configuration) 

work-hours × $85 

per hour = Between 

$7,990 and $9,945.

Between $22,994 and 

$30,197 (depending 

on airplane configuration).

Between $30,984 and 

$40,142.

538 Between $16,669,392 

and $21,596,396. 

Placard installation, if 

necessary.

1 work-hour × $85 per 

hour = $85.

$10 .............................. $95 .............................. 685 $65,075. 

AFM revision ................. 1 work-hour × $85 per 

hour = $85.

None ............................ $85 .............................. 538 $45,730. 

Installation of secondary 

pump control relays 

(Boeing Alert Service 

Bulletin 737– 

28A1248).

68 work-hours × $85 

per hour = $5,780.

$3,274 ......................... $9,054 ......................... 685 $6,201,990. 

AWL revision to add 

28–AWL–23.

1 work-hour × $85 per 

hour = $85.

None ............................ $85 .............................. 685 $58,225. 

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 

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 adding 

the following new airworthiness 

directive (AD): 

2011–18–03 The Boeing Company: 

Amendment 39–16785; Docket No. 

FAA–2007–28661; Directorate Identifier 

2007–NM–013–AD. 

Effective Date 

(a) This AD is effective September 30, 

2011. 

Affected ADs 

(b) Accomplishing certain requirements of 

this AD terminates certain requirements of 

AD 2001–08–24, Amendment 39–12201 (66 

FR 20733, April 25, 2001); AD 2002–24–51, 

Amendment 39–12992 (68 FR 10, January 2, 

2003); and AD 2008–24–51, Amendment 39– 

15781 (74 FR 8155, February 24, 2009). 

Airworthiness Directive 2002–19–52, 

Amendment 39–12900 (67 FR 61253, 

September 30, 2002), is affected by this AD. 

Applicability 

(c) This AD applies to the airplanes, 

certificated in any category, identified in 

paragraphs (c)(1) and (c)(2) of this AD. 

(1) The Boeing Company Model 737–600, 

–700, –700C, –800, and –900 series airplanes, 

identified in Boeing Alert Service Bulletin 

737–28A1206, Revision 2, dated May 21, 

2009. 

(2) The Boeing Company Model 737–600, 

–700, –700C, –800, and –900 series airplanes, 

identified in Boeing Alert Service Bulletin 

737–28A1248, Revision 2, dated August 28, 

2009. 

Note 1: This AD requires revisions to 

certain operator maintenance documents to 

include new inspections. Compliance with 

these inspections is required by 14 CFR 

91.403(c). For airplanes that have been 

previously modified, altered, or repaired in 

the areas addressed by these inspections, the 

operator may not be able to accomplish the 

inspections described in the revisions. In this 

situation, to comply with 14 CFR 91.403(c), 

the operator must request approval for an 

alternative method of compliance (AMOC) 

according to paragraph (u) of this AD. The 

request should include a description of 

changes to the required inspections that will 

ensure the continued operational safety of 

the airplane. 

Subject 

(d) Joint Aircraft System Component 

(JASC)/Air Transport Association (ATA) of 

America Code 28, Fuel. 

Unsafe Condition 

(e) This AD was prompted by fuel system 

reviews conducted by the manufacturer. We 

are issuing this AD to prevent center tank 

fuel pump operation with continuous low 

pressure, which could lead to friction sparks 

or overheating in the fuel pump inlet that 

could create a potential ignition source 

inside the center fuel tank. These conditions, 

in combination with flammable fuel vapors, 

could result in a center fuel tank explosion 

and consequent loss of the airplane. 

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Federal Register / Vol. 76, No. 166 / Friday, August 26, 2011 / Rules and Regulations 53321 

Compliance 

(f) Comply with this AD within the 

compliance times specified, unless already 

done. 

Installation of Automatic Shutoff System for 

the Center Tank Fuel Boost Pumps 

(g) For airplanes identified in paragraph 

1.A.1. of Boeing Alert Service Bulletin 737– 

28A1206, Revision 2, dated May 21, 2009: 

Within 36 months after the effective date of 

this AD, install an automatic shutoff system 

for the center tank fuel boost pumps, by 

accomplishing all of the actions specified in 

Part 1 and Part 2 of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–28A1206, Revision 2, dated May 21, 

2009, except that Figure 1 of this AD must 

be used in lieu of Sheet 2 of Figure 11 of 

Boeing Alert Service Bulletin 737–28A1206, 

Revision 2, dated May 21, 2009. If a placard 

has been previously installed on the airplane 

in accordance with paragraph (h) of this AD, 

the placard may be removed from the flight 

deck of only that airplane after the automatic 

shutoff system has been installed. Installing 

automatic shutoff systems on all airplanes in 

an operator’s fleet, in accordance with this 

paragraph, terminates the placard installation 

required by paragraph (h) of this AD for all 

airplanes in an operator’s fleet. 

Note 2: Boeing Alert Service Bulletin 737– 

28A1206, Revision 2, dated May 21, 2009, 

refers to Boeing Component Service Bulletin 

233A3202–28–03, dated January 12, 2006, as 

an additional source of guidance for 

replacing the left and right center boost 

pump switches of the P5–2 fuel control 

module assembly with new switches and 

changing the wiring of the P5–2 fuel control 

module assembly. 

BILLING CODE 4910–13–P 

BILLING CODE 4910–13–C 

Placard Installation for Mixed Fleet 

Operation 

(h) Prior to or concurrently with installing 

an automatic shutoff system on any airplane 

in an operator’s fleet, as required by 

paragraph (g) of this AD, install a placard 

adjacent to the pilot’s primary flight display 

on all airplanes in the operator’s fleet that are 

not equipped with an automatic shutoff 

system for the center tank fuel boost pumps. 

The placard must read as follows (unless 

alternative placard wording is approved by 

an appropriate FAA Principal Operations 

Inspector): 

‘‘AD 2002–24–51 fuel usage restrictions 

required.’’ 

Installing an automatic shutoff system, in 

accordance with paragraph (g) of this AD, 

terminates the placard installation required 

by this paragraph for only that airplane. 

Installing automatic shutoff systems on all 

airplanes in an operator’s fleet, in accordance 

with paragraph (g) of this AD, terminates the 

placard installation required by this 

paragraph for all airplanes in an operator’s 


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53322 Federal Register / Vol. 76, No. 166 / Friday, August 26, 2011 / Rules and Regulations 

fleet. If operation according to the fuel usage 

restrictions of AD 2002–24–51, Amendment 

39–12992 (68 FR 10, January 2, 2003), and 

AD 2001–08–24, Amendment 39–12201 (66 

FR 20733, April 25, 2001), is maintained 

until automatic shutoff systems are installed 

on all airplanes in an operator’s fleet, the 

placard installation specified in this 

paragraph is not required. Installation of a 

placard in accordance with paragraph (e) of 

AD 2002–19–52, Amendment 39–12900 (67 

FR 61253, September 30, 2002), is acceptable 

for compliance with the placard installation 

requirements of this paragraph; however, 

terminating action specified in paragraph (g) 

of AD 2002–19–52 and installation of an 

automatic shutoff system required by 

paragraph (g) of this AD must be 

accomplished on the airplane before the 

placard is removed from the airplane. 

Airplane Flight Manual (AFM) Revision 

(i) For airplanes on which Boeing Alert 

Service Bulletin 737–28A1206, Revision 2, 

dated May 21, 2009, has been accomplished: 

At the applicable time specified in paragraph 

(i)(1) or (i)(2) of this AD, do the actions 

specified in paragraphs (i)(3) and (i)(4) of this 

AD. 

(1) For airplanes on which the terminating 

action specified in paragraph (g) of AD 2002– 

19–52, Amendment 39–12900 (67 FR 61253, 

September 30, 2002), has been done: 

Concurrently with accomplishing the actions 

required by paragraph (g) of this AD. 

(2) For airplanes on which the terminating 

action specified in paragraph (g) of AD 2002– 

19–52, Amendment 39–12900 (67 FR 61253, 

September 30, 2002), has not been done: 

Concurrently with accomplishing the 

terminating action specified in paragraph (g) 

of AD 2002–19–52. 

(3) Revise Section 1 of the Limitations 

section of the Boeing 737–600/–700/–700C/– 

800/–900 AFM to include the following 

statement. This may be done by inserting a 

copy of this AD into the AFM. 

‘‘Center Tank Fuel Pumps 

Intentional dry running of a center tank 

fuel pump (low pressure light illuminated) is 

prohibited.’’ 

Note 3: For clarification purposes, the AFM 

limitations required by AD 2002–19–52, 

Amendment 39–12900 (67 FR 61253, 

September 30, 2002), continue to be required 

until the optional terminating actions 

specified in paragraph (g) of AD 2002–19–52 

have been done. 

(4) Revise Section 3 of the Normal 

Procedures section of the Boeing 737–600/ 

–700/–700C/–800/–900 AFM to include the 

following statements. This may be done by 

inserting a copy of this AD into the AFM. 

Alternative statements that meet the intent of 

the following requirements may be used if 

approved by an appropriate FAA Principal 

Operations Inspector. 

‘‘CENTER TANK FUEL PUMPS 

Alternative Method of Compliance (AMOC) 

to AD 2001–08–24 and AD 2002–24–51 for 

Aircraft With the Automated Center Tank 

Fuel Pump Shutoff 

Center tank fuel pumps must not be ‘‘ON’’ 

unless personnel are available in the flight 

deck to monitor low pressure lights. 

For ground operation, center tank fuel 

pump switches must not be positioned ‘‘ON’’ 

unless the center tank fuel quantity exceeds 

1000 pounds (453 kilograms), except when 

defueling or transferring fuel. Upon 

positioning the center tank fuel pump 

switches ‘‘ON’’ verify momentary 

illumination of each center tank fuel pump 

low pressure light. 

For ground and flight operations, the 

corresponding center tank fuel pump switch 

must be positioned ‘‘OFF’’ when a center 

tank fuel pump low pressure light 

illuminates [1]. Both center tank fuel pump 

switches must be positioned ‘‘OFF’’ when the 

first center tank fuel pump low pressure light 

illuminates if the center tank is empty. 

[1] When established in a level flight 

attitude, both center tank pump switches 

should be positioned ‘‘ON’’ again if the 

center tank contains usable fuel. 

Defueling and Fuel Transfer 

When transferring fuel or defueling center 

or main tanks, the fuel pump low pressure 

lights must be monitored and the fuel pumps 

positioned to ‘‘OFF’’ at the first indication of 

the fuel pump low pressure [1]. 

Defueling the main tanks with passengers 

on board is prohibited if the main tank fuel 

pumps are powered [2]. 

Defueling the center tank with passengers 

on board is prohibited if the center tank fuel 

pumps are powered and the auto-shutoff 

system is inhibited [2]. 

[1] Prior to transferring fuel or defueling, 

conduct a lamp test of the respective fuel 

pump low pressure lights. 

[2] Fuel may be transferred from tank to 

tank or the aircraft may be defueled with 

passengers on board, provided fuel quantity 

in the tank from which fuel is being taken is 

maintained at or above 2000 pounds (907 

kilograms).’’ 

Note 4: When statements identical to those 

in paragraphs (i)(3) and (i)(4) of this AD have 

been included in the general revisions of the 

Boeing 737–600/–700/–700C/–800/–900 

AFM, the general revisions may be inserted 

into that AFM, and the copy of this AD may 

be removed from that AFM. 

Installation of Secondary Pump Control 

Relays 

(j) For airplanes identified in paragraph 

1.A.1. of Boeing Alert Service Bulletin 737– 

28A1248, Revision 2, dated August 28, 2009: 

Within 60 months after the effective date of 

this AD, install one secondary control relay 

for the electrical control circuit of each of the 

two center tank fuel boost pumps, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–28A1248, Revision 2, dated August 28, 

2009. 

Airworthiness Limitations (AWL) Revision 

for AWL No. 28–AWL–23 

(k) For airplanes identified in paragraph 

1.A.1. of Boeing Alert Service Bulletin 737– 

28A1248, Revision 2, dated August 28, 2009: 

Concurrently with accomplishing the actions 

required by paragraph (j) of this AD, or 

within 30 days after the effective date of this 

AD, whichever occurs later, revise the 

maintenance program by incorporating AWL 

No. 28–AWL–23 of Subsection E, AWLs— 

Fuel Systems, of Section 9, Airworthiness 

Limitations (AWLs) and Certification 

Maintenance Requirements (CMRs), of the 

Boeing 737–600/700/800/900 MPD 

Document, D626A001–CMR, Revision March 

2011. The initial compliance time for the 

actions specified in AWL No. 28–AWL–23 is 

within 1 year after accomplishing the 

installation required by paragraph (j) of this 

AD, or within 1 year after the effective date 

of this AD, whichever occurs later. 

No Alternative Inspections or Inspection 

Intervals 

(l) After accomplishing the applicable 

actions specified in paragraph (k) of this AD, 

no alternative inspections or inspection 

intervals may be used unless the inspections 

or inspection intervals are approved as an 

AMOC in accordance with the procedures 

specified in paragraph (u) of this AD. 

Terminating Action for AD 2001–08–24, 

Amendment 39–12201 (66 FR 20733, April 

25, 2001) 

(m) Accomplishing the actions required by 

paragraphs (g), (h), and (i) of this AD, or 

accomplishing the actions specified in 

paragraph (s) of this AD, terminates the 

requirements of paragraph (a) of AD 2001– 

08–24, Amendment 39–12201 (66 FR 20733, 

April 25, 2001), for Model 737–600, –700, 

–700C, –800, and –900 series airplanes that 

have the automatic shutoff system, or a TDG 

Aerospace, Inc., universal fault interrupter 

(UFI), installed. After accomplishing the 

actions required by paragraphs (g), (h), and 

(i) of this AD, or accomplishing the actions 

specified in paragraph (s) of this AD, the 

AFM limitation required by paragraph (a) of 

AD 2001–08–24 may be removed from the 

AFM for those airplanes. 

Terminating Action for AD 2002–24–51, 

Amendment 39–12992 (68 FR 10, January 2, 

2003) 

(n) Accomplishing the actions required by 

paragraphs (g), (h), and (i) of this AD, or 

accomplishing the actions specified in 

paragraph (s) of this AD, terminates the 

requirements of paragraph (b) of AD 2002– 

24–51, Amendment 39–12992 (68 FR 10, 

January 2, 2003), for Model 737–600, –700, 

–700C, –800, and –900 series airplanes that 

have the automatic shutoff system, or a TDG 

Aerospace, Inc., UFI, installed. After 

accomplishing the actions required by 

paragraphs (g), (h), and (i) of this AD, or 

accomplishing the actions specified in 

paragraph (s) of this AD, the AFM limitations 

required by paragraph (b) of AD 2002–24–51 

may be removed from the AFM for those 

airplanes. 

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Federal Register / Vol. 76, No. 166 / Friday, August 26, 2011 / Rules and Regulations 53323 

Terminating Action for AWL Revision 

(o) Incorporating AWL No. 28–AWL–23 

into the maintenance program in accordance 

with paragraph (g)(3) of AD 2008–10–10 R1, 

Amendment 39–16164 (75 FR 1529, January 

12, 2010), terminates the corresponding 

action required by paragraph (k) of this AD. 

Terminating Action for AD 2008–24–51, 

Amendment 39–15781 (74 FR 8155, 

February 24, 2009) 

(p) Accomplishing the actions required by 

paragraph (g) of this AD terminates the 

requirements of paragraph (f) of AD 2008– 

24–51, Amendment 39–15781 (74 FR 8155, 

February 24, 2009). 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(q) Actions accomplished before the 

effective date of this AD in accordance with 

Boeing Alert Service Bulletin 737–28A1248, 

dated December 21, 2006; or Boeing Alert 

Service Bulletin 737–28A1248, Revision 1, 

dated January 9, 2008; are considered 

acceptable for compliance with the 

corresponding actions specified in paragraph 

(j) of this AD. 

(r) Actions accomplished before the 

effective date of this AD in accordance with 

Boeing Alert Service Bulletin 737–28A1206, 

dated January 11, 2006; or Revision 1, dated 

January 30, 2008; are considered acceptable 

for compliance with the corresponding 

actions specified in paragraph (g) of this AD, 

provided one of the actions specified in 

paragraph (r)(1) or (r)(2) of this AD have been 

done. 

(1) The procedures specified in paragraph 

(f) of AD 2008–24–51, Amendment 39–15781 

(74 FR 8155, February 24, 2009), have been 

accomplished. 

(2) The actions specified in Part 3 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–28A1206, Revision 2, 

dated May 21, 2009, have been 

accomplished. 

Optional Terminating Action 

(s) Installing TDG Aerospace, Inc., UFI, in 

accordance with a method approved by the 

Manager, Seattle Aircraft Certification Office 

(ACO), FAA, within 36 months after the 

effective date of this AD, terminates the 

actions required by paragraphs (g) through (k) 

of this AD; provided that, concurrently with 

installing a UFI on any airplane in an 

operator’s fleet, a placard is installed 

adjacent to the pilot’s primary flight display 

on all airplanes in the operator’s fleet not 

equipped with a UFI or an automatic shutoff 

system. The placard must read as follows 

(unless alternative placard wording is 

approved by an appropriate FAA Principal 

Operations Inspector): 

‘‘AD 2002–24–51 fuel usage restrictions 

required.’’ 

Installation of a placard in accordance with 

paragraph (h) of this AD is acceptable for 

compliance with the placard installation 

required by this paragraph. Installing a TDG 

Aerospace, Inc., UFI in accordance with this 

paragraph on an airplane terminates the 

placard installation required by this 

paragraph for only that airplane. Installing 

TDG Aerospace, Inc., UFIs in accordance 

with this paragraph, or automatic shutoff 

systems in accordance with paragraph (g) of 

this AD, on all airplanes in an operator’s fleet 

terminates the placard installation required 

by this paragraph for all airplanes in an 

operator’s fleet. If operation according to the 

fuel usage restrictions of AD 2002–24–51, 

Amendment 39–12992 (68 FR 10, January 2, 

2003), and AD 2001–08–24, Amendment 39– 

12201 (66 FR 20733, April 25, 2001), is 

maintained until UFIs or automatic shutoff 

systems are installed on all airplanes in an 

operator’s fleet, the placard installation 

specified in this paragraph is not required. 

Installation of a placard in accordance with 

paragraph (e) of AD 2002–19–52, 

Amendment 39–12900 (67 FR 61253, 

September 30, 2002), is acceptable for 

compliance with the placard installation 

requirements of this paragraph; however, 

terminating action specified in paragraph (g) 

of AD 2002–19–52 and installation of a UFI 

specified by this paragraph must be 

accomplished on the airplane before the 

placard is removed from the airplane. 

Note 5: Guidance on installing a TDG 

Aerospace, Inc., UFI can be found in TDG 

Aerospace, Inc., Supplemental Type 

Certificate (STC) ST02076LA. 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(t) Revising the maintenance program by 

incorporating AWL No. 28–AWL–23 of a 

revision specified in paragraphs (t)(1) 

through (t)(12) of this AD of Subsection G, 

Airworthiness Limitations—Fuel System 

AWLs, of Section 9, Airworthiness 

Limitations (AWLs) and Certification 

Maintenance Requirements (CMRs), of the 

Boeing 737–600/700/800/900 MPD 

Document, D626A001–CMR; or Subsection E, 

AWLs—Fuel Systems, of Section 9, 

Airworthiness Limitations (AWLs) and 

Certification Maintenance Requirements 

(CMRs), of the Boeing 737–600/700/800/900 

MPD Document, D626A001–CMR, Revision 

February 2011; before the effective date of 

this AD is considered acceptable for 

compliance with the corresponding actions 

specified in paragraph (k) of this AD. 

(1) Revision March 2008. 

(2) Revision April 2008. 

(3) Revision June 2008. 

(4) Revision February 2009. 

(5) Revision March 2009. 

(6) Revision August 2009. 

(7) Revision September 2009. 

(8) Revision November 2009. 

(9) Revision January 2010. 

(10) Revision May 2010. 

(11) Revision July 2010. 

(12) Revision August 2010. 

Alternative Methods of Compliance 

(AMOCs) 

(u)(1) The Manager, Seattle 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 e-mailed 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. 

Related Information 

(v) For more information about this AD, 

contact Tak Kobayashi, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind Ave., 

SW., Renton, Washington 98057–3356; 

phone: (425) 917–6499; fax (425) 917–6590; 

e-mail: Takahisa.Kobayashi@faa.gov. 

Material Incorporated by Reference 

(w) You must use the service information 

contained in table 1 of this AD, as applicable, 

to do the actions required by this AD, unless 

the AD specifies otherwise. 

TABLE 1—ALL MATERIAL INCORPORATED BY REFERENCE

Document Revision Date 

Boeing Alert Service Bulletin 737–28A1206 ............................................................................................ 2 ............................ May 21, 2009. 

Boeing Alert Service Bulletin 737–28A1248 ............................................................................................ 2 ............................ August 28, 2009. 

AWL No. 28–AWL–23 of Subsection E, AWLs—Fuel Systems of Section 9, Airworthiness Limitations 

(AWLs) and Certification Maintenance Requirements (CMRs), of the Boeing 737–600/700/800/900 

Maintenance Planning Data Document, D626A001–CMR.

March 2011 ........... March 2011. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

the service information contained in table 1 

of this AD under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) For Boeing 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 

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53324 Federal Register / Vol. 76, No. 166 / Friday, August 26, 2011 / Rules and Regulations 

206–766–5680; e-mail 

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 August 

12, 2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–21617 Filed 8–25–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0823; Directorate 

Identifier 2011–SW–018–AD; Amendment 

39–16765; AD 2011–17–01] 

RIN 2120–AA64 

Airworthiness Directives; Agusta 

S.p.A. Model A109A, A109A II, A109C, 

and A109K2 Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: This amendment supersedes 

an existing emergency airworthiness 

directive (EAD) for the specified Agusta 

S.p.A. (Agusta) model helicopters. That 

EAD currently requires inspecting the 

main rotor scissor fitting assembly to 

determine if there are 2 washers 

installed under the head of each main 

rotor scissor fitting assembly fixing bolt 

(fixing bolt). If there are not 2 washers 

installed under the head of each fixing 

bolt, that EAD requires replacing each 

fixing bolt and installing 2 washers 

under the head of each fixing bolt. This 

superseding airworthiness directive 

(AD) is prompted by the determination 

that a wrong part number (P/N) for the 

main rotor scissor fitting assembly was 

listed in the EAD. This AD retains the 

requirements of the EAD and corrects a 

P/N for the main rotor scissor fitting 

assembly. The actions specified by this 

AD are intended to prevent a crack in 

a fixing bolt, failure of a fixing bolt, and 

subsequent loss of control of the 

helicopter. 

DATES: Effective September 12, 2011. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of September 

12, 2011. 

Comments for inclusion in the Rules 

Docket must be received on or before 

October 25, 2011. 

ADDRESSES: Use one of the following 

addresses to submit comments on this 

AD: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue, SE., Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue, SE., Washington, DC 20590, 

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

through Friday, except Federal holidays. 

You may get the service information 

identified in this AD from Agusta 

Westland, Customer Support & Services, 

Via Per Tornavento 15, 21019 Somma 

Lombardo (VA) Italy, ATTN: Giovanni 

Cecchelli; telephone 39- 0331–711133; 

fax 39 0331 711180; or at http:// 

www.agustawestland.com/technicalbullettins. 

Examining the Docket: You may 

examine the docket that contains the 

AD, any comments, and other 

information on the Internet at http:// 

www.regulations.gov, or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The Docket 

Operations office (telephone (800) 647– 

5527) is located in Room W12–140 on 

the ground floor of the West Building at 

the street address stated in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

DOT/FAA Southwest Region, Sharon 

Miles, Aviation Safety Engineer, 

Rotorcraft Directorate, Regulations and 

Policy Group, ASW–111, 2601 

Meacham Blvd., Fort Worth, Texas 

76137, telephone (817) 222–5122, fax 

(817) 222–5961. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On January 13, 2010, we issued EAD 

2010–02–51 for the Agusta Model 

A109A, A109A II, A109C, and A109K2 

helicopters, which requires, within 5 

hours time-in-service (TIS), inspecting 

the main rotor scissor fitting assembly, 

P/N 109–0110–67 and P/N 109–0110– 

58, to determine if there were 2 washers 

installed under the head of each fixing 

bolt, P/N 109–0101–78–5. That action 

was prompted by an incident where 2 

of the 3 installed fixing bolts on a Model 

A109K2 helicopter had cracked in 

flight. The manufacturer’s investigation 

revealed that the crack was caused by 

inadequate information in the technical 

publication for installing the fixing 

bolts. This condition, if not detected 

and corrected, could result in failure of 

a fixing bolt and subsequent loss of 

control of the helicopter. 

Since issuing EAD 2010–02–51, we 

have determined that the EAD contains 

an incorrect P/N for the main rotor 

scissor fitting assembly as listed in 

paragraph (a) of the Compliance section. 

The EAD states P/N ‘‘109–0110–58’’ and 

the correct P/N is ‘‘109–0101–58’’. 

Therefore, we are issuing this 

superseding AD to correct a P/N for the 

main rotor scissor fitting assembly. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Emergency AD 

2009–0274–E, dated December 18, 2009 

(EAD 2009–0274–E) to correct an unsafe 

condition for the Agusta Model A109A, 

A109A II, A109C, and A109K2 model 

helicopters. EASA states that failure of 

the fixing bolt ‘‘might lead to loss of 

control of the helicopter.’’ 

Related Service Information 

Agusta has issued Mandatory Alert 

Bollettino Tecnico (BT) No. 109K–53 for 

Model A109K2 helicopters and 

Mandatory Alert BT No. 109–131 for 

Model A109A, A109A II, and A109C 

helicopters, both dated December 18, 

2009. The BTs specify a one-time 

inspection for correct installation of the 

main rotor scissor fitting assembly by 

determining if 2 washers are installed 

under the head of each fixing bolt. If 2 

washers are not installed under the head 

of each fixing bolt, the BTs specify 

replacing each fixing bolt with an 

airworthy fixing bolt and installing 2 

washers under the head of each fixing 

bolt. EASA classified this service 

bulletin as mandatory and issued EAD 

No. 2009–0274–E to ensure the 

continued airworthiness of these 

helicopters. 

FAA’s Evaluation and Unsafe Condition 

Determination 

These helicopters have been approved 

by the aviation authority of Italy, and 

are approved for operation in the United 

States. Pursuant to our bilateral 

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