Federal Register / Vol. 70, No. 220 / Wednesday, November 16, 2005 / Rules and Regulations 69427 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD. See the ADDRESSES section for 

a location to examine the regulatory 

evaluation. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

2005–23–17 Boeing: Amendment 39–14375. 

Docket No. FAA–2004–19539; 

Directorate Identifier 2004–NM–06–AD. 

Effective Date 

(a) This AD becomes effective December 

21, 2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to the Boeing airplanes 

listed in Table 1 of this AD, certificated in 

any category: 

TABLE 1.—APPLICABILITY

Airplane Line numbers 

Model 737–100, –200, –200C, –300, –400, and –500 series airplanes ................................................................... 1 through 3132 inclusive. 

Model 737–600, –700, –700C, –800, and –900 series airplanes ............................................................................. 0001 through 1240 inclusive. 

Unsafe Condition 

(d) This AD was prompted by evidence of 

chafed wiring behind the P15 refuel panel 

and arcing to the back of the P15 refuel panel 

and adjacent wing structure. We are issuing 

this AD to detect and correct chafing of the 

wiring behind the P15 refuel panel, which 

could lead to arcing and fire with consequent 

airplane damage and injury to refueling 

personnel. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Inspection and Corrective Actions 

(f) Within 18 months after the effective 

date of this AD, perform the following 

actions as applicable: 

(1) For Model 737–100, –200, –200C, –300, 

–400, and –500 series airplanes: Perform a 

one-time detailed inspection of the wires in 

wire bundle W0024 to connector D04578P on 

the back of the P15 refuel panel for 

discrepancies, and do any applicable 

corrective and related investigative actions 

before further flight, in accordance with the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 737–28–

1193, Revision 1, dated July 28, 2005. 

(2) For Model 737–600, –700, –700C, –800, 

and –900 series airplanes: Perform all 

applicable actions listed in paragraphs 

(f)(2)(i) and (f)(2)(ii) of this AD in accordance 

with the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

737–28–1200, Revision 1, dated July 28, 

2005. 

(i) For Group 1 and Group 2 airplanes as 

defined in Service Bulletin 737–28–1200: 

Perform a one-time detailed inspection for 

discrepancies of the clamp and T-bolt 

assembly on the wing thermal anti-ice duct 

near the P15 refuel panel and do any 

applicable corrective actions before further 

flight. 

(ii) For Group 2 airplanes only as defined 

in Service Bulletin 737–28–1200: Perform a 

one-time detailed inspection for 

discrepancies of the wires in wire bundle 

W0024 to connector D04578P on the back of 

the P15 refuel panel and do any applicable 

corrective actions before further flight. 

Note 1: For the purposes of this AD, a 

detailed inspection is: ‘‘An intensive visual 

examination of a specific structural area, 

system, installation, or assembly to detect 

damage, failure, or irregularity. Available 

lighting is normally supplemented with a 

direct source of good lighting at intensity 

deemed appropriate by the inspector. 

Inspection aids such as mirror, magnifying 

lenses, etc., may be used. Surface cleaning 

and elaborate access procedures may be 

required.’’

Credit for Actions Done Previously 

(g) Actions accomplished before the 

effective date of this AD in accordance with 

Boeing Special Attention Service Bulletin 

737–28–1193, dated April 24, 2003; or 

Boeing Special Attention Service Bulletin 

737–28–1200, dated July 10, 2003; as 

applicable; including Information Notices 

737–28–1193 IN 01 and 737–28–1200 IN 01; 

both dated September 11, 2003; as 

applicable, are acceptable for compliance 

with the corresponding actions required by 

this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(h)(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested in accordance with the procedures 

found in 14 CFR 39.19. 

(2) Before using any AMOC approved in 

accordance with 14 CFR 39.19 on any 

airplane to which the AMOC applies, notify 

the appropriate principal inspector in the 

FAA Flight Standards Certificate Holding 

District Office. 

Material Incorporated by Reference 

(i) You must use Boeing Special Attention 

Service Bulletin 737–28–1193, Revision 1, 

dated July 28, 2005; or Boeing Special 

Attention Service Bulletin 737–28–1200, 

Revision 1, dated July 28, 2005; as 

applicable; to perform the actions that are 

required by this AD, unless the AD specifies 

otherwise. The Director of the Federal 

Register approved the incorporation by 

reference of these documents in accordance 

with 5 U.S.C. 552(a) and 1 CFR part 51. 

Contact Boeing Commercial Airplanes, P.O. 

Box 3707, Seattle, Washington 98124–2207, 

for a copy of this service information. You 

may review copies at the Docket Management 

Facility, U.S. Department of Transportation, 

400 Seventh Street SW., room PL–401, Nassif 

Building, Washington, DC; on the Internet at 

http://dms.dot.gov; or at the National 

Archives and Records Administration 

(NARA). For information on the availability 

of this material at the NARA, 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 7, 2005. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 05–22591 Filed 11–15–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–22972; Directorate 

Identifier 2003–NM–265–AD; Amendment 

39–14376; AD 2005–23–18] 

RIN 2120–AA64 

Airworthiness Directives; Fokker 

Model F27 Mark 050 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

69428 Federal Register / Vol. 70, No. 220 / Wednesday, November 16, 2005 / Rules and Regulations 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for all 

Fokker Model F27 Mark 050 airplanes. 

This AD requires a one-time inspection 

of the bleed air supply ducts to 

determine if blanking plugs are present 

and a one-time inspection of the entire 

area of the engine nacelle for heat 

damage; and corrective actions if 

necessary. This AD also requires 

replacement of the blanking plugs with 

clamping devices. This AD results from 

heat damage in areas adjacent to the 

bleed air supply duct assembly. We are 

issuing this AD to prevent rupture of the 

bleed air supply duct, which could lead 

to hot bleed air leaking into the engine 

controls area and result in heat damage 

to control cables, electrical wiring, 

hydraulic components, and fuel lines, 

and consequent fire. 

DATES: This AD becomes effective 

December 1, 2005. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of December 1, 2005. 

We must receive comments on this 

AD by January 17, 2006. 

ADDRESSES: Use one of the following 

addresses to submit comments on this 

AD. 

• DOT Docket Web site: Go to 

http://dms.dot.gov and follow the 

instructions for sending your comments 

electronically. 

• Government-wide rulemaking Web 

site: Go to http://www.regulations.gov 

and follow the instructions for sending 

your comments electronically. 

• Mail: Docket Management Facility; 

U.S. Department of Transportation, 400 

Seventh Street SW., Nassif Building, 

room PL–401, Washington, DC 20590. 

• Fax: (202) 493–2251. 

• Hand Delivery: Room PL–401 on 

the plaza level of the Nassif Building, 

400 Seventh Street SW., Washington, 

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

through Friday, except Federal holidays. 

Contact Fokker Services B.V., P.O. 

Box 231, 2150 AE Nieuw-Vennep, the 

Netherlands, for service information 

identified in this AD. 

FOR FURTHER INFORMATION CONTACT: Tom 

Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–1137; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The Civil Aviation Authority—The 

Netherlands (CAA–NL), which is the 

airworthiness authority for the 

Netherlands, notified us that an unsafe 

condition may exist on all Fokker Model 

F27 Mark 050 airplanes. The CAA–NL 

advises that an operator found heat 

damage in areas adjacent to the bleed air 

supply duct assembly while inspecting 

for hydraulic leakage in the engine 

controls area on a Model F27 Mark 050 

airplane. The same operator also found 

a second airplane with heat damage 

after inspecting its remaining fleet. 

Further investigation revealed that the 

inner wall of the bleed air supply duct 

was ruptured, which caused bleed air to 

escape and blow out the three blanking 

plugs that are fitted on the outer wall of 

the bleed air supply duct. As a result, 

hot bleed air vented into the engine 

controls area through the holes in the 

outer wall (created by the blown out 

blanking plugs) of the bleed air supply 

duct. This condition, if not corrected, 

could result in heat damage to control 

cables, electrical wiring, hydraulic 

components, and fuel lines, and 

consequent fire. 

Relevant Service Information 

Fokker Services B.V. has issued 

Service Bulletin SBF50–36–006, dated 

October 1, 2001. The service bulletin 

describes the procedures for inspecting 

zones 431 and 441 of the engine 

controls area to determine if the 

blanking plugs are installed in place on 

the outer ducts of the bleed air supply 

duct assemblies and doing corrective 

actions if necessary. The corrective 

actions include the following: 

• If the blanking plugs are missing 

and bleed air loss is evident (i.e., the 

bleed air supply duct has burned spots, 

discoloration, or deformation), visually 

inspecting the components adjacent to 

the bleed air supply duct assemblies for 

heat damage (part C of the 

accomplishment instructions) and 

replacing the blanking plugs of the 

bleed air supply duct with clamping 

devices (part D of the accomplishment 

instructions). 

• If bleed air loss is not evident, 

replacing the blanking plugs of the 

bleed air supply duct with clamping 

devices. 

• If there is leakage from the bleed air 

supply duct due to a ruptured inner 

duct, replacing the bleed air supply duct 

assembly with a serviceable bleed air 

supply duct assembly (i.e, one that has 

had the blanking plugs replaced with 

clamping devices). 

• If there is a loss of corrosionpreventing compound from the engine 

control cables, cleaning the cables, 

inspecting for discoloration, and 

applying the corrosion-preventing 

compound. 

• If advice is needed for repairing 

heat damage to a component, wiring, or 

structures, contacting the manufacturer 

for additional instructions. 

Accomplishing the actions specified 

in the service information is intended to 

adequately address the unsafe 

condition. The CAA–NL mandated the 

service information and issued Dutch 

airworthiness directive 2001–130, dated 

October 31, 2001, to ensure the 

continued airworthiness of these 

airplanes in the Netherlands. 

FAA’s Determination and Requirements 

of This AD 

This airplane models is manufactured 

in the Netherlands and is type 

certificated for operation in the United 

States under the provisions of section 

21.29 of the Federal Aviation 

Regulations (14 CFR 21.29) and the 

applicable bilateral airworthiness 

agreement. Pursuant to this bilateral 

airworthiness agreement, the CAA–NL 

has kept the FAA informed of the 

situation described above. We have 

examined the CAA–NL’s findings, 

evaluated all pertinent information, and 

determined that we need to issue an AD 

for products of this type design that are 

certificated for operation in the United 

States. 

Therefore, we are issuing this AD to 

prevent rupture of the bleed air supply 

duct, which could lead to hot bleed air 

leaking into the engine controls area and 

result in heat damage to control cables, 

electrical wiring, hydraulic components, 

and fuel lines, and consequent fire. This 

AD requires accomplishing the actions 

specified in the service information 

described previously, except as 

discussed under ‘‘Difference Between 

the AD and Service Bulletin.’’

Difference Between the AD and Service 

Bulletin 

The service bulletin specifies to 

contact the manufacturer for 

instructions on how to repair certain 

conditions, but this AD would require 

repairing those conditions using a 

method that we or the CAA–NL (or its 

delegated agent) approve. In light of the 

type of repair that would be required to 

address the unsafe condition, and 

consistent with existing bilateral 

airworthiness agreements, we have 

determined that, for this AD, a repair we 

or the CAA–NL approve would be 

acceptable for compliance with this AD. 

Clarification of Inspection Terminology 

The inspection and ‘‘visual 

inspection’’ specified in the Fokker 

service bulletin is referred to as a 

‘‘general visual inspection’’ in this AD. 

We have included the definition for a 

general visual inspection in a note in 

this AD. 

Federal Register / Vol. 70, No. 220 / Wednesday, November 16, 2005 / Rules and Regulations 69429 

Costs of Compliance 

None of the airplanes affected by this 

action are on the U.S. Register. All 

airplanes affected by this AD are 

currently operated by non-U.S. 

operators under foreign registry; 

therefore, they are not directly affected 

by this AD action. However, we 

consider this AD necessary to ensure 

that the unsafe condition is addressed if 

any affected airplane is imported and 

placed on the U.S. Register in the future. 

If an affected airplane is imported and 

placed on the U.S. Register in the future, 

the required actions would take about 3 

work hours per airplane, at an average 

labor rate of $65 per work hour. Based 

on these figures, the estimated cost of 

the AD would be $195 per airplane. 

FAA’s Determination of the Effective 

Date 

No airplane affected by this AD is 

currently on the U.S. Register. 

Therefore, providing notice and 

opportunity for public comment is 

unnecessary before this AD is issued, 

and this AD may be made effective in 

less than 30 days after it is published in 

the Federal Register. 

Comments Invited 

This AD is a final rule that involves 

requirements that affect flight safety and 

was not preceded by notice and an 

opportunity for public comment; 

however, we invite you to submit any 

relevant written data, views, or 

arguments regarding this AD. Send your 

comments to an address listed in the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2005–22972; Directorate Identifier 

2003–NM–265–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of the AD that might suggest a 

need to modify it. 

We will post all comments we 

receive, without change, to http:// 

dms.dot.gov, including any personal 

information you provide. We will also 

post a report summarizing each 

substantive verbal contact with FAA 

personnel concerning this AD. Using the 

search function of that Web site, anyone 

can find and read the comments in any 

of our dockets, including the name of 

the individual who sent the comment 

(or signed the comment on behalf of an 

association, business, labor union, etc.). 

You may review the DOT’s complete 

Privacy Act Statement in the Federal 

Register published on April 11, 2000 

(65 FR 19477–78), or you may visit 

http://dms.dot.gov. 

Examining the Docket 

You may examine the AD docket on 

the Internet at http://dms.dot.gov, or in 

person at the Docket Management 

Facility office between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. The Docket 

Management Facility office (telephone 

(800) 647–5227) is located on the plaza 

level of the Nassif Building at the DOT 

street address stated in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after the Docket 

Management System receives them. 

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 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); and 

3. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

See the ADDRESSES section for a location 

to examine the regulatory evaluation. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The Federal Aviation 

Administration (FAA) amends § 39.13 

by adding the following new 

airworthiness directive (AD): 

2005–23–18 Fokker Services B.V.: 

Amendment 39–14376. Docket No. 

FAA–2005–22972; Directorate Identifier 

2003–NM–265–AD. 

Effective Date 

(a) This AD becomes effective December 1, 

2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to all Fokker Model 

F27 Mark 050 airplanes, certificated in any 

category. 

Unsafe Condition 

(d) This AD results from heat damage in 

areas adjacent to the bleed air supply duct 

assembly. We are issuing this AD to prevent 

rupture of the bleed air supply duct, which 

could lead to hot bleed air leaking into the 

engine controls area and result in heat 

damage to control cables, electrical wiring, 

hydraulic components, and fuel lines, and 

consequent fire. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

General Visual Inspection 

(f) At the applicable compliance time 

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

AD, do a general visual inspection of the 

bleed air supply to determine if blanking 

plugs are present and a general visual 

inspection of the entire area of the engine 

nacelle for any heat damage, and do any 

corrective actions as applicable, by 

accomplishing all of the applicable actions 

specified in parts B and C of the 

Accomplishment Instructions of Fokker 

Service Bulletin SBF50–36–006, dated 

October 1, 2001; except as provided by 

paragraph (g) of this AD. Any corrective 

actions must be done before further flight. 

69430 Federal Register / Vol. 70, No. 220 / Wednesday, November 16, 2005 / Rules and Regulations 

Note 1: For the purposes of this AD, a 

general visual inspection is: ‘‘A visual 

examination of an interior or exterior area, 

installation, or assembly to detect obvious 

damage, failure, or irregularity. This level of 

inspection is made from within touching 

distance unless otherwise specified. A mirror 

may be necessary to ensure visual access to 

all surfaces in the inspection area. This level 

of inspection is made under normally 

available lighting conditions such as 

daylight, hangar lighting, flashlight, or 

droplight and may require removal or 

opening of access panels or doors. Stands, 

ladders, or platforms may be required to gain 

proximity to the area being checked.’’

(1) For airplanes that have accumulated 

20,000 total flight hours or more as of the 

effective date of this AD: Within 6 months 

after the effective date of this AD. 

(2) For airplanes that have accumulated 

less than 20,000 total flight hours as of the 

effective date of this AD: Within 12 months 

after the effective date of this AD. 

(g) If, during accomplishment of the 

corrective actions required by paragraph (f) of 

this AD, the service bulletin requires 

contacting the manufacturer for instructions 

on repairing heat damage to a component, 

wiring, or structure: Before further flight, 

repair according to a method approved by 

either the Manager, International Branch, 

ANM–116, FAA, Transport Airplane 

Directorate; or the Civil Aviation Authority—

The Netherlands (or its delegated agent). 

Modification 

(h) Before further flight after accomplishing 

the inspection required by paragraph (f) of 

this AD: Replace the blanking plugs of the 

bleed air supply ducts with clamping 

devices, in accordance with Part D of the 

Accomplishment Instructions of Fokker 

Service Bulletin SBF50–36–006, dated 

October 1, 2001. 

Alternative Methods of Compliance 

(AMOCs) 

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

ANM–116, Transport Airplane Directorate, 

FAA, has the authority to approve AMOCs 

for this AD, if requested in accordance with 

the procedures found in 14 CFR 39.19. 

(2) Before using any AMOC approved in 

accordance with 14 CFR 39.19 on any 

airplane to which the AMOC applies, notify 

the appropriate principal inspector in the 

FAA Flight Standards Certificate Holding 

District Office. 

Related Information 

(j) Dutch airworthiness directive 2001–130, 

dated October 31, 2001, also addresses the 

subject of this AD. 

Material Incorporated by Reference 

(k) You must use Fokker Service Bulletin 

SBF50–36–006, dated October 1, 2001, to 

perform the actions that are required by this 

AD, unless the AD specifies otherwise. The 

Director of the Federal Register approved the 

incorporation by reference of this document 

in accordance with 5 U.S.C. 552(a) and 1 CFR 

part 51. Contact Fokker Services B.V., P.O. 

Box 231, 2150 AE Nieuw-Vennep, the 

Netherlands, for a copy of this service 

information. You may review copies at the 

Docket Management Facility, U.S. 

Department of Transportation, 400 Seventh 

Street, SW., room PL–401, Nassif Building, 

Washington, DC; on the Internet at http:// 

dms.dot.gov; or at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at the NARA, 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 7, 2005. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 05–22589 Filed 11–15–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–22427; Directorate 

Identifier 2004–NM–263–AD; Amendment 

39–14373; AD 2005–23–15] 

RIN 2120–AA64 

Airworthiness Directives; British 

Aerospace Model BAC 1–11 200 and 

400 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for all 

British Aerospace Model BAC 1–11 200 

and 400 series airplanes. This AD 

requires revising the airplane flight 

manual (AFM) to contain applicable 

AFM amendments, which advise the 

flightcrew of information pertaining to 

safely operating the fuel system. The AD 

also requires revising the FAA-approved 

maintenance program to include certain 

repetitive maintenance tasks intended to 

improve the safety of the fuel system. 

This AD results from fuel system 

reviews conducted by the manufacturer. 

We are issuing this AD to prevent 

potential ignition sources inside the fuel 

system, which, in combination with 

flammable fuel vapors, could result in a 

fuel tank explosion and consequent loss 

of the airplane. 

DATES: This AD becomes effective 

December 21, 2005. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of December 21, 2005. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

dms.dot.gov or in person at the Docket 

Management Facility, U.S. Department 

of Transportation, 400 Seventh Street, 

SW., Nassif Building, room PL–401, 

Washington, DC. 

Contact British Aerospace, Service 

Support, Airbus Limited, P.O. Box 77, 

Bristol BS99 7AR, England, for service 

information identified in this AD. 

FOR FURTHER INFORMATION CONTACT: 

Todd Thompson, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98055–4056; telephone 

(425) 227–1175; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Examining the Docket 

You may examine the airworthiness 

directive (AD) docket on the Internet at 

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

Docket Management Facility office 

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

through Friday, except Federal holidays. 

The Docket Management Facility office 

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

the plaza level of the Nassif Building at 

the street address stated in the 

ADDRESSES section. 

Discussion 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to all British Aerospace Model 

BAC 1–11 200 and 400 series airplanes. 

That NPRM was published in the 

Federal Register on September 16, 2005 

(70 FR 54671). That NPRM proposed to 

require revising the airplane flight 

manual (AFM) to contain applicable 

AFM amendments, which advise the 

flightcrew of information pertaining to 

safely operating the fuel system. The 

NPRM also proposed to require revising 

the FAA-approved maintenance 

program to include certain repetitive 

maintenance tasks intended to improve 

the safety of the fuel system. 

Clarification of Alternative Method of 

Compliance (AMOC) Paragraph 

We have revised this action to clarify 

the appropriate procedure for notifying 

the principal inspector before using any 

approved AMOC on any airplane to 

which the AMOC applies. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We received no 

comments on the NPRM or on the 

determination of the cost to the public. 

Conclusion 

We have carefully reviewed the 

available data and determined that air