12122 Federal Register / Vol. 71, No. 46 / Thursday, March 9, 2006 / Rules and Regulations 

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): 

2006–05–10 BAE Systems (Operations) 

Limited (Formerly British Aerospace 

Regional Aircraft): Amendment 39–

14507. Docket No. FAA–2005–23477; 

Directorate Identifier 2005–NM–181–AD. 

Effective Date 

(a) This AD becomes effective April 13, 

2006. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to BAE Systems 

(Operations) Limited Model BAe 146–100A, 

–200A, and –300A series airplanes, and 

Model Avro 146–RJ70A, 146–RJ85A, and 

146–RJ100A airplanes; certificated in any 

category; as identified in BAE Systems 

(Operations) Limited Inspection Service 

Bulletin ISB.52–113, Revision 1, dated 

February 11, 2005. 

Unsafe Condition 

(d) This AD results from in-service reports 

of hinge bracket failures on the main landing 

gear (MLG) doors. We are issuing this AD to 

prevent failure of the hinge bracket on the 

MLG door, which could result in separation 

of the door, consequent structural damage to 

the airplane, and possible injury to people on 

the ground. 

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/Corrective Action 

(f) At the applicable time specified in 

paragraph (f)(1) or (f)(2) of this AD: Perform 

a one-time detailed inspection for corrosion 

of the hinge bracket assembly of the left and 

right MLG doors by doing all the applicable 

actions in accordance with the 

Accomplishment Instructions of BAE 

Systems (Operations) Limited Inspection 

Service Bulletin ISB.52–113, Revision 1, 

dated February 11, 2005. Perform any 

applicable corrective action before further 

flight in accordance with the service bulletin. 

If no corrosion is found, before further flight, 

apply protective treatment in accordance 

with the service bulletin. 

(1) For airplanes on which the date of 

issuance of the original standard 

airworthiness certificate or the date of 

issuance of the original export certificate of 

airworthiness is on or before February 28, 

1991: Within 192 months since the date of 

issuance of the original standard 

airworthiness certificate or the date of 

issuance of the original export certificate of 

airworthiness, or within 12 months after the 

effective date of this AD, whichever is later. 

(2) For airplanes on which the date of 

issuance of the original standard 

airworthiness certificate or the date of 

issuance of the original export certificate of 

airworthiness is after February 28, 1991: 

Within 24 months after the effective date of 

this AD. 

Note 1: For the purposes of this AD, a 

detailed inspection is: ‘‘An intensive 

examination of a specific item, installation, 

or assembly to detect damage, failure, or 

irregularity. Available lighting is normally 

supplemented with a direct source of good 

lighting at an intensity deemed appropriate. 

Inspection aids such as mirror, magnifying 

lenses, etc., may be necessary. Surface 

cleaning and elaborate procedures may be 

required.’’

Inspections Accomplished According to 

Previous Issue of Service Bulletin 

(g) Inspections accomplished before the 

effective date of this AD in accordance with 

BAE Systems (Operations) Limited 

Inspection Service Bulletin ISB.52–113, 

dated February 2, 2001, are considered 

acceptable for compliance with the 

corresponding action specified in this AD. 

Parts Installation 

(h) As of the effective date of this AD, no 

person may install, on any airplane, a hinge 

bracket assembly of the left and right MLG 

doors, unless it has been inspected (and any 

corrective actions done) according to BAE 

Systems (Operations) Limited Inspection 

Service Bulletin ISB.52–113, Revision 1, 

dated February 11, 2005. 

No Reporting Required 

(i) Although BAE Systems (Operations) 

Limited Inspection Service Bulletin ISB.52–

113, Revision 1, dated February 11, 2005, 

referenced in this AD, specifies to submit 

certain information to the manufacturer, this 

AD does not include that requirement. 

Alternative Methods of Compliance 

(AMOCs) 

(j)(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 § 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 

(k) British airworthiness directive G–2005–

0017, dated July 6, 2005, also addresses the 

subject of this AD. 

Material Incorporated by Reference 

(l) You must use BAE Systems (Operations) 

Limited Inspection Service Bulletin ISB.52–

113, Revision 1, dated February 11, 2005, 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 British Aerospace Regional 

Aircraft American Support, 13850 Mclearen 

Road, Herndon, Virginia 20171, 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 February 

24, 2006. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 06–2141 Filed 3–8–06; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–23196; Directorate 

Identifier 2005–NM–187–AD; Amendment 

39–14506; AD 2006–05–09] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 747–200C, –200F, –400, –400D, 

and –400F 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 certain 

Boeing Model 747–200C, –200F, –400, 

–400D, and –400F series airplanes. This 

AD requires repetitive inspections for 

cracks in the overlapping (upper) skin, 

upper fastener row of the lap joints of 

the fuselage skin in sections 41, 42, and 

46; and related investigative and 

corrective actions, if necessary. This AD 

results from fatigue tests and an analysis 

that identified areas of the fuselage lap 

joints where fatigue cracks can occur. 

We are issuing this AD to detect and 

correct fatigue cracks in the overlapping 

(upper) skin, upper fastener row of the 

lap joints of the fuselage skin in sections 

41, 42, and 46, which could adversely 


hsrobinson on PROD1PC70 with RULES
Federal Register / Vol. 71, No. 46 / Thursday, March 9, 2006 / Rules and Regulations 12123 

affect the structural integrity of the 

airplane. 

DATES: This AD becomes effective 

April 13, 2006. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of April 13, 2006. 

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 Boeing Commercial 

Airplanes, P.O. Box 3707, Seattle, 

Washington 98124–2207, for service 

information identified in this AD. 

FOR FURTHER INFORMATION CONTACT: Nick 

Kusz, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 917–6432; 

fax (425) 917–6590. 

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 certain Boeing Model 747–

200C, –200F, –400, –400D, and –400F 

series airplanes. That NPRM was 

published in the Federal Register on 

December 6, 2005 (70 FR 72599). That 

NPRM proposed to require repetitive 

inspections for cracks in the 

overlapping (upper) skin, upper fastener 

row of the lap joints of the fuselage skin 

in sections 41, 42, and 46; and related 

investigative and corrective actions, if 

necessary. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comment received. The 

commenter, Boeing, supports the 

NPRM. 

Conclusion 

We have carefully reviewed the 

available data, including the comment 

received, and determined that air safety 

and the public interest require adopting 

the AD as proposed. 

Costs of Compliance 

There are about 796 airplanes of the 

affected design in the worldwide fleet. 

This AD affects about 153 airplanes of 

U.S. registry. The required inspections 

will take about 534 work hours per 

airplane, at an average labor rate of $65 

per work hour. Based on these figures, 

the estimated cost of the AD for U.S. 

operators is $5,310,630, or $34,710 per 

airplane, per inspection cycle. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. Subtitle VII, 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in subtitle VII, 

part A, subpart III, section 44701, 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We have determined that this AD will 

not have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

(2) Is not a ‘‘significant rule’’ under 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 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): 

2006–05–09 Boeing: Amendment 39–14506. 

Docket No. FAA–2005–23196; 

Directorate Identifier 2005–NM–187–AD. 

Effective Date 

(a) This AD becomes effective April 13, 

2006. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Boeing Model 747–

200C, –200F, –400, –400D, and –400F series 

airplanes, certificated in any category; as 

identified in Boeing Alert Service Bulletin 

747–53A2499, dated August 11, 2005. 

Unsafe Condition 

(d) This AD results from fatigue tests and 

an analysis that identified areas of the 

fuselage lap joints where fatigue cracks can 

occur. We are issuing this AD to detect and 

correct fatigue cracks in the overlapping 

(upper) skin, upper fastener row of the lap 

joints of the fuselage skin in sections 41, 42, 

and 46, which could adversely affect the 

structural integrity of the airplane. 

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. 

Initial Inspections and Related Investigative 

and Corrective Actions 

(f) At the applicable time specified in Table 

1 of this AD: Do an external surface high 

frequency eddy current (HFEC), external low 

frequency eddy current (LFEC), and internal 

LFEC inspection, as applicable, for cracks in 

the overlapping (upper) skin, upper fastener 

row of the lap joints of the fuselage skin in 

sections 41, 42, and 46, and any applicable 

related investigative and corrective actions 

by doing all of the actions in accordance with 

the Accomplishment Instructions of Boeing 


hsrobinson on PROD1PC70 with RULES
12124 Federal Register / Vol. 71, No. 46 / Thursday, March 9, 2006 / Rules and Regulations 

Alert Service Bulletin 747–53A2499, dated 

August 11, 2005, except as provided by 

paragraph (h) of this AD. Do any applicable 

related investigative and corrective actions 

before further flight. 

TABLE 1.—INITIAL COMPLIANCE TIME

For airplanes on which Structural Significant Items (SSIs) F–25G, F– 

25H, and F–25I— Inspect— 

(1) Have not been inspected in accordance with paragraph (d) of AD 

2004–07–22, amendment 39–13566 (69 FR 24063, May 3, 2004), 

using the HFEC method.

Before the accumulation of 22,000 total flight cycles, or within 1,000 

flight cycles after the effective date of this AD, whichever occurs 

later. 

(2) Have been inspected in accordance with paragraph (d) of AD 

2004–07–22, using the HFEC method.

Within 3,000 flight cycles after the most recent supplemental structural 

inspection document (SSID) inspection of each applicable structural 

significant item (as given in Boeing Document D6–35022, ‘‘SSID for 

Model 747 Airplanes,’’ Revision G, dated December 2000), or within 

1,000 flight cycles after the effective date of this AD, whichever occurs later. 

Repetitive Inspections 

(g) Repeat the applicable inspections 

required by paragraph (f) of this AD 

thereafter at intervals not to exceed those 

specified in paragraph 1.E., ‘‘Compliance’’

(including the note) of Boeing Alert Service 

Bulletin 747–53A2499, dated August 11, 

2005. 

Exception to Service Bulletin Instructions 

(h) Where the service bulletin specifies to 

contact Boeing for appropriate action, before 

further flight, repair the crack using a method 

approved in accordance with the procedures 

specified in paragraph (i) of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(i)(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 § 39.19 on any airplane to 

which the AMOC applies, notify the 

appropriate principal inspector in the FAA 

Flight Standards Certificate Holding District 

Office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD, if it is approved by an 

Authorized Representative for the Boeing 

Commercial Airplanes Delegation Option 

Authorization Organization who has been 

authorized by the Manager, Seattle ACO, to 

make those findings. For a repair method to 

be approved, the repair must meet the 

certification basis of the airplane, and the 

approval must specifically refer to this AD. 

Material Incorporated by Reference 

(j) You must use Boeing Alert Service 

Bulletin 747–53A2499, dated August 11, 

2005, 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 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 February 

27, 2006. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 06–2142 Filed 3–8–06; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–23357; Directorate 

Identifier 2005–NM–207–AD; Amendment 

39–14505; AD 2006–05–08] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 777–200 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 certain 

Boeing Model 777–200 series airplanes. 

This AD requires installing a new 

washer between the lower wing surface 

and the jam nut of the sump drain valve 

assembly. This AD results from fuel 

system reviews conducted by the 

manufacturer. We are issuing this AD to 

prevent energy from a lightning strike 

on the bushing for the sump drain valve 

from arcing to the inside of the center 

fuel tank wall, which could create an 

ignition source in the fuel tank and 

result in a fuel tank explosion. 

DATES: This AD becomes effective April 

13, 2006. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of April 13, 2006. 

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 Boeing Commercial 

Airplanes, P.O. Box 3707, Seattle, 

Washington 98124–2207, for service 

information identified in this AD. 

FOR FURTHER INFORMATION CONTACT: 

Margaret Langsted, Aerospace Engineer, 

Propulsion Branch, ANM–140S, Seattle 

Aircraft Certification Office, FAA, 1601 

Lind Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 917–6500; 

fax (425) 917–6590. 

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 certain Boeing Model 777–200 

series airplanes. That NPRM was 

published in the Federal Register on 

December 20, 2005 (70 FR 75428). That 

NPRM proposed to require installing a 

new washer between the lower wing 


hsrobinson on PROD1PC70 with RULES