Federal Register / Vol. 75, No. 29 / Friday, February 12, 2010 / Proposed Rules 6865 

accordance with the Accomplishment Instructions of the applicable service bulletin 

listed in Table 1 of this AD. 

TABLE 1—SERVICE BULLETINS

Airplane model— 

Bombardier 

Service 

Bulletin— 

Revision— Dated— 

CL–600–1A11 (CL–600) ................................................................................................................. 600–0742 01 July 6, 2009. 

CL–600–2A12 (CL–601) ................................................................................................................. 601–0597 01 July 6, 2009. 

CL–600–2B16 (CL–601–3A, CL–601–3R variant).

CL–600–2B16 (CL–604 variant) ..................................................................................................... 604–29–008 01 July 6, 2009. 

CL–600–2B16 (CL–605) ................................................................................................................. 605–29–001 01 July 6, 2009. 

(i) For each accumulator (P/Ns 08–60163– 

001, 08–60163–002, 08–60164–001, and 08– 

60164–002) that has accumulated more than 

3,650 total flight cycles as of the effective 

date of this AD, replace the accumulator 

within 100 flight cycles after the effective 

date of this AD. 

(ii) For each accumulator (P/Ns 08–60163– 

001, 08–60163–002, 08–60164–001, and 08– 

60164–002) that has accumulated 3,650 total 

flight cycles or fewer as of the effective date 

of this AD, replace the accumulator before 

the accumulation of 3,750 total flight cycles 

on the accumulator. 

(iii) For each accumulator (P/Ns 08–60163– 

001, 08–60163–002, 08–60164–001, and 08– 

60164–002) for which it is not possible to 

determine the number of flight cycles 

accumulated, replace the accumulator within 

100 flight cycles after the effective date of 

this AD. 

(3) Thereafter, before the accumulation of 

3,750 total flight cycles on any accumulator 

having P/N 08–60163–001, 08–60163–002, 

08–60164–001, or 08–60164–002, replace the 

accumulator with a new accumulator having 

the same part number, in accordance with 

the Accomplishment Instructions of the 

applicable service bulletin listed in Table 1 

of this AD. 

(4) Replacement of an accumulator with a 

new accumulator having the same part 

number is also acceptable for compliance 

with the requirements of paragraph (g)(2) of 

this AD, if done before the effective date of 

this AD in accordance with the applicable 

service bulletin listed in Table 2 of this AD: 

TABLE 2—PREVIOUS SERVICE BULLETINS

Airplane model— 

Bombardier 

Service 

Bulletin— 

Dated— 

CL–600–1A11 (CL–600) .............................................................................................................................. 600–0742 November 10, 2008. 

CL–600–2A12 (CL–601) .............................................................................................................................. 601–0597 November 10, 2008. 

CL–600–2B16 (CL–601–3A, CL–601–3R variant).

CL–600–2B16 (CL–604 variant) .................................................................................................................. 604–29–008 November 10, 2008. 

CL–600–2B16 (CL–605) .............................................................................................................................. 605–29–001 November 10, 2008. 

FAA AD Differences 

Note 2: This AD differs from the MCAI 

and/or service information as follows: 

(1) The MCAI specifies that certain 

airplanes do not need to be inspected for the 

part number; however, this AD requires that 

inspections be done on all airplanes to 

determine the part number. 

(2) The MCAI specifies to record the 

number of flight cycles accumulated on each 

affected part. This AD does not require that 

operators record the number of flight cycles. 

Other FAA AD Provisions 

(h) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

Certification Office (ACO), ANE–170, FAA, 

has the authority to approve AMOCs for this 

AD, if requested using the procedures found 

in 14 CFR 39.19. Send information to ATTN: 

Program Manager, Continuing Operational 

Safety, FAA, New York ACO, 1600 Stewart 

Avenue, Suite 410, Westbury, New York, 

11590; telephone 516–228–7300; fax 516– 

794–5531. Before using any approved AMOC 

on any airplane to which the AMOC applies, 

notify your principal maintenance inspector 

(PMI) or principal avionics inspector (PAI), 

as appropriate, or lacking a principal 

inspector, your local Flight Standards District 

Office. The AMOC approval letter must 

specifically reference this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, under the 

provisions of the Paperwork Reduction Act 

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

Management and Budget (OMB) has 

approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(i) Refer to MCAI Canadian Airworthiness 

Directive CF–2009–39, dated October 27, 

2009, and the service bulletins listed in Table 

1 of this AD, for related information. 

Issued in Renton, Washington, on February 

5, 2010. 

Stephen P. Boyd, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–2993 Filed 2–11–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0037; Directorate 

Identifier 2009–NM–240–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 737–700 (IGW) Series 

Airplanes Equipped With Auxiliary Fuel 

Tanks Installed in Accordance With 

Configuration 3 of Supplemental Type 

Certificate ST00936NY 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 


cprice-sewell on DSK2BSOYB1PROD with PROPOSALS
6866 Federal Register / Vol. 75, No. 29 / Friday, February 12, 2010 / Proposed Rules 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Model 737–700 (IGW) series airplanes. 

This proposed AD would require 

deactivation or modification of PATS 

Aircraft, LLC, auxiliary fuel tanks. This 

proposed AD results from fuel system 

reviews conducted by the manufacturer. 

We are proposing this AD to prevent the 

potential of ignition sources inside fuel 

tanks, which, in combination with 

flammable fuel vapors, could result in 

fuel tank explosions and consequent 

loss of the airplane. 

DATES: We must receive comments on 

this proposed AD by March 29, 2010. 

ADDRESSES: You may send comments by 

any of the following methods: 

• 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. 

For service information identified in 

this proposed AD, contact Decrane 

Aerospace, PATS Aircraft Systems, 

21652 Nanticoke Avenue, Georgetown, 

Delaware 19947; telephone 302–253– 

6157; fax 302–855–0153; e-mail 

giuseppecoppola@

decraneaerospace.com; Internet http:// 

www.decraneaerospace.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 

or 425–227–1152. 

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 proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(telephone 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Mazdak Hobbi, Aerospace Engineer, 

Propulsion and Services Branch, ANE– 

173, FAA, New York Aircraft 

Certification Office, 1600 Stewart 

Avenue, Suite 410, Westbury, New York 

11590; telephone (516) 228–7330; fax 

(516) 794–5531. 

SUPPLEMENTARY INFORMATION:

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2010–0037; Directorate Identifier 

2009–NM–240–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD because of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

The FAA has examined the 

underlying safety issues involved in fuel 

tank explosions on several large 

transport airplanes, including the 

adequacy of existing regulations, the 

service history of airplanes subject to 

those regulations, and existing 

maintenance practices for fuel tank 

systems. As a result of those findings, 

we issued a regulation titled ‘‘Transport 

Airplane Fuel Tank System Design 

Review, Flammability Reduction and 

Maintenance and Inspection 

Requirements’’ (66 FR 23086, May 7, 

2001). In addition to new airworthiness 

standards for transport airplanes and 

new maintenance requirements, this 

rule included Special Federal Aviation 

Regulation No. 88 (‘‘SFAR 88,’’ 

Amendment 21–78, and subsequent 

Amendments 21–82 and 21–83). 

Among other actions, SFAR 88 

requires certain type design (i.e., type 

certificate (TC) and supplemental type 

certificate (STC)) holders to substantiate 

that their fuel tank systems can prevent 

ignition sources in the fuel tanks. This 

requirement applies to type design 

holders for large turbine-powered 

transport airplanes and for subsequent 

modifications to those airplanes. It 

requires them to perform design reviews 

and to develop design changes and 

maintenance procedures if their designs 

do not meet the new fuel tank safety 

standards. As explained in the preamble 

to the rule, we intended to adopt 

airworthiness directives to mandate any 

changes found necessary to address 

unsafe conditions identified as a result 

of these reviews. 

In evaluating these design reviews, we 

have established four criteria intended 

to define the unsafe conditions 

associated with fuel tank systems that 

require corrective actions. The 

percentage of operating time during 

which fuel tanks are exposed to 

flammable conditions is one of these 

criteria. The other three criteria address 

the failure types under evaluation: 

single failures, single failures in 

combination with a latent condition(s), 

and in-service failure experience. For all 

four criteria, the evaluations included 

consideration of previous actions taken 

that may mitigate the need for further 

action. 

We have determined that the actions 

identified in this AD are necessary to 

reduce the potential of ignition sources 

inside fuel tanks, which, in combination 

with flammable fuel vapors, could result 

in fuel tank explosions and consequent 

loss of the airplane. 

Supplemental Type Certificates (STCs) 

for PATS Aircraft, LLC, Auxiliary Fuel 

Tanks 

The auxiliary fuel tank STC on 

affected airplanes is of two basic type 

designs: A box-and-bladder type, and a 

double-walled cylindrical type. The 

box-and-bladder tanks are emptied and 

vented into the airplane center wing 

tank using either pneumatic air pressure 

supplied from the airplane, or electrical 

power from the airplane to power fuel 

pumps installed in the tank external dry 

bay area. The double-walled cylindrical 

tanks use pneumatic air pressure to 

empty into the airplane center wing 

tank. All auxiliary tanks use some type 

of electrical fuel quantity indication 

system (FQIS), flight deck control and 

annunciation panels, float level 

switches, valves and venting systems, 

electrical wiring connections in the dry 

bay area, and electrical bonding 

methods. 

FAA’s Findings 

During the SFAR 88 safety 

assessment, it was determined that the 

PATS Aircraft, LLC, FQIS and float level 

switch did not meet intrinsically safe 

electrical energy levels as described in 

the guidelines of Advisory Circular (AC) 

25.981–1C, ‘‘Fuel Tank Ignition Source 

Prevention Guidelines.’’ PATS Aircraft, 

LLC, the STC holder, identified 

potential ignition sources resulting from 

a combination of single and latent 


cprice-sewell on DSK2BSOYB1PROD with PROPOSALS
Federal Register / Vol. 75, No. 29 / Friday, February 12, 2010 / Proposed Rules 6867 

failures for the PATS Aircraft, LLC, fuel 

tank subsystems. PATS Aircraft, LLC, 

has not complied with the requirements 

of SFAR 88, paragraph 2. To prevent 

high electrical energy levels from the 

FQIS and float level switch from 

entering the auxiliary fuel tank, we have 

determined that the appropriate 

solution for continued use is a 

combination of actions. Installing a 

transient suppression device (TSD) on 

FQIS and float level switches would be 

needed. In order to maximize wire 

separation, the TSD must be installed as 

close as possible to the points where the 

FQIS and float level switch wires exit 

the TSD and enter the auxiliary tank. 

Other actions might include replacing 

high-energy FQISs, and float level 

switches that are impractical for TSD 

application, with intrinsically safe 

FQISs, providing wire separation, 

conducting a one-time inspection and/ 

or replacing aging float level switch 

conduit assemblies, periodically 

inspecting the external dry bay system 

components and wires, and testing the 

integrity of bonding resistances. 

As an alternative to the modification 

described above, deactivation of the 

auxiliary fuel tanks would adequately 

address the unsafe condition. If 

operators do not wish to deactivate their 

auxiliary fuel tanks, we will consider 

requests for alternative methods of 

compliance (AMOCs). The most likely 

requests would be to allow continued 

use of the tanks by showing compliance 

with SFAR 88. This would involve 

obtaining STCs to modify the auxiliary 

fuel tank systems and developing 

maintenance procedures to address the 

safety issues identified above. PATS 

Aircraft, LLC, as the current STC holder, 

may be working on AMOCs. Operators 

may contact PATS or propose an AMOC 

on their own. 

Once an operator has deactivated a 

tank as proposed by this NPRM, the 

operator might wish to remove the tank. 

This would require a separate design 

approval, if an approved tank removal 

procedure does not exist. 

Relevant Service Information 

We have reviewed Decrane Aerospace 

Service Bulletins ST00936NY–D–28– 

SB–001_K, dated August 25, 2008; and 

ST00936NY–D–28–SB–021_K, dated 

January 8, 2009; which describe 

procedures for modifying the auxiliary 

fuel system (AFS). The modification of 

the auxiliary fuel cells of the AFS 

specified in Decrane Aerospace Service 

Bulletin ST00936NY–D–28–SB–001_K 

includes removing, repositioning, 

replacing or adding bonding jumpers 

and/or hardware. The modification of 

the AFS harnesses specified in Decrane 

Aerospace Service Bulletin 

ST00936NY–D–28–SB–021_K includes 

removing and replacing the auxiliary 

fuel system critical harnesses. 

FAA’s Determination and Requirements 

of the Proposed AD 

We have evaluated all pertinent 

information and identified an unsafe 

condition that is likely to exist or 

develop on other products of this same 

type design. For this reason, we are 

proposing this AD, which would require 

deactivation to prevent usage of 

auxiliary fuel tanks, or modification of 

the auxiliary fuel system. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 11 airplanes of U.S. 

registry. We also estimate that it would 

take about 250 work-hours per product 

to comply with this proposed AD. The 

average labor rate is $85 per work-hour. 

Required parts would cost about 

$10,000 per product. Based on these 

figures, we estimate the cost of this 

proposed AD to the U.S. operators to be 

$343,750, or $31,250 per product. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would not have a 

substantial direct effect on the States, on 

the relationship between the national 

Government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this proposed 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), and 

3. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

You can find our regulatory 

evaluation and the estimated costs of 

compliance in the AD Docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

2. The FAA amends § 39.13 by adding 

the following new AD: 

The Boeing Company: Docket No. FAA– 

2010–0037; Directorate Identifier 2009– 

NM–240–AD. 

Comments Due Date 

(a) We must receive comments by March 

29, 2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to The Boeing 

Company Model 737–700 (IGW) series 

airplanes, certificated in any category; 

equipped with auxiliary fuel tanks installed 

in accordance with configuration 3 of 

Supplemental Type Certificate ST00936NY. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 28: Fuel. 

Unsafe Condition 

(e) This AD results from fuel system 

reviews conducted by the manufacturer. The 

Federal Aviation Administration is issuing 

this AD to prevent the potential of ignition 

sources inside fuel tanks, which, in 

combination with flammable fuel vapors, 

could result in fuel tank explosions and 

consequent loss of the airplane. 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 


cprice-sewell on DSK2BSOYB1PROD with PROPOSALS
6868 Federal Register / Vol. 75, No. 29 / Friday, February 12, 2010 / Proposed Rules 

Prevent Usage of Auxiliary Fuel Tanks or 

Modify Auxiliary Fuel System 

(g) Within 45 days after the effective date 

of this AD: Accomplish the requirements 

specified in paragraph (g)(1) or (g)(2) of this 

AD. 

(1) Deactivate the auxiliary fuel tanks, in 

accordance with a deactivation procedure 

approved by the Manager, New York Aircraft 

Certification Office (ACO). Any auxiliary 

tank component that remains on the airplane 

must be secured and must have no effect on 

the continued operational safety and 

airworthiness of the airplane. Deactivation 

must not result in the need for additional 

instructions for continued airworthiness. 

Note 1: Appendix A of this AD provides 

criteria that should be included in the 

deactivation procedures. The proposed 

deactivation procedures should be submitted 

to the Manager, New York ACO, as soon as 

possible to ensure timely review and 

approval. 

Note 2: For technical information, contact 

Mazdak Hobbi, Aerospace Engineer, 

Propulsion and Services Branch, ANE–173, 

FAA, New York Aircraft Certification Office 

(ACO), 1600 Stewart Avenue, Suite 410, 

Westbury, New York 11590; telephone 516– 

228–7330; fax 516–794–5531. 

(2) Modify the auxiliary fuel system by 

doing all the applicable actions in 

accordance with the Accomplishment 

Instructions of Decrane Aerospace Service 

Bulletin ST00936NY–D–28–SB–001_K, dated 

August 25, 2008; and Decrane Aerospace 

Service Bulletin ST00936NY–D–28–SB– 

021_K, dated January 8, 2009. 

Reporting Requirement 

(h) Within 45 days after the effective date 

of this AD, submit a report to the Manager, 

New York ACO. The report must include the 

information listed in paragraphs (h)(1), (h)(2), 

and (h)(3) of this AD. Under the provisions 

of the Paperwork Reduction Act (44 U.S.C. 

3501 et seq.), the Office of Management and 

Budget (OMB) has approved the information 

collection requirements contained in this AD, 

and assigned OMB Control Number 2120– 

0056. 

(1) The airplane registration and operation 

status. 

(2) The usage frequency in terms of total 

number of flights per year and total number 

of flights per year for which the auxiliary 

tank is used. 

(3) Method of complying with paragraph 

(g)(1) of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(i)(1) The Manager, New York ACO, ANE– 

170, FAA, has the authority to approve 

AMOCs for this AD, if requested using the 

procedures found in 14 CFR 39.19. Send 

information to Attn: Program Manager, 

Continuing Operational Safety, FAA, New 

York ACO, 1600 Stewart Avenue, Suite 410, 

Westbury, New York 11590; telephone 516– 

228–7300; fax 516–794–5531. Before using 

any approved AMOC on any airplane to 

which the AMOC applies, notify your 

principal maintenance inspector (PMI) or 

principal avionics inspector (PAI), as 

appropriate, or lacking a principal inspector, 

your local Flight Standards District Office. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your principal maintenance inspector 

(PMI) or principal avionics inspector (PAI), 

as appropriate, or lacking a principal 

inspector, your local Flight Standards District 

Office. The AMOC approval letter must 

specifically reference this AD. 

Appendix A 

Deactivation Criteria 

The auxiliary fuel tank deactivation 

procedures required by paragraph (g)(1) of 

this AD should address the following actions. 

(1) Permanently drain auxiliary fuel tanks, 

and clear them of fuel vapors to eliminate the 

possibility of out-gassing of fuel vapors from 

the emptied auxiliary tank. 

(2) Disconnect all electrical connections 

from the fuel quantity indication system 

(FQIS), fuel pumps if applicable, float 

switches, and all other electrical connections 

required for auxiliary tank operation, and 

stow them at the auxiliary tank interface. 

(3) Disconnect all pneumatic connections if 

applicable, cap them at the pneumatic 

source, and secure them. 

(4) Disconnect all fuel feed and fuel vent 

plumbing interfaces with airplane original 

equipment manufacturer (OEM) tanks, cap 

them at the airplane tank side, and secure 

them in accordance with a method approved 

by the FAA; one approved method is 

specified in AC 25–8 Auxiliary Fuel System 

Installations. In order to eliminate the 

possibility of structural deformation during 

cabin decompression, leave open and secure 

the disconnected auxiliary fuel tank vent 

lines. 

(5) Pull and collar all circuit breakers used 

to operate the auxiliary tank. 

(6) Revise the weight and balance 

document, if required, and obtain FAA 

approval. 

(7) Amend the applicable sections of the 

applicable airplane flight manual (AFM) to 

indicate that the auxiliary fuel tank is 

deactivated. Remove auxiliary fuel tank 

operating procedures to ensure that only the 

OEM fuel system operational procedures are 

contained in the AFM. Amend the 

Limitations Section of the AFM to indicate 

that the AFM Supplement for the STC is not 

in effect. Place a placard in the flight deck 

indicating that the auxiliary tank is 

deactivated. The AFM revisions specified in 

this paragraph may be accomplished by 

inserting a copy of this AD into the AFM. 

(8) Amend the applicable sections of the 

applicable flight crew operating manual and 

airplane maintenance manual to remove 

auxiliary tank maintenance procedures. 

(9) After the auxiliary fuel tank is 

deactivated, accomplish procedures such as 

leak checks and pressure checks deemed 

necessary before returning the airplane to 

service. These procedures must include 

verification that the airplane FQIS and fuel 

distribution systems have not been adversely 

affected. 

(10) Revise the instructions for continued 

airworthiness, as required, after deactivation. 

(11) Include with the operator’s proposed 

procedures any relevant information or 

additional steps that are deemed necessary 

by the operator to comply with the 

deactivation and return the airplane to 

service. 

Issued in Renton, Washington, on February 

5, 2010. 

Stephen P. Boyd, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–2994 Filed 2–11–10; 8:45 am] 

BILLING CODE 4910–13–P 


cprice-sewell on DSK2BSOYB1PROD with PROPOSALS