Federal Register / Vol. 70, No. 225 / Wednesday, November 23, 2005 / Rules and Regulations 70715 

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): 

2005–24–03 Boeing: Amendment 39–14383. 

Docket No. FAA–2005–19682; 

Directorate Identifier 2004–NM–88–AD. 

Effective Date 

(a) This AD becomes effective December 

28, 2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Boeing Model 737–

600, –700, –700C, and –800 series airplanes; 

line numbers 1 through 761 inclusive, except 

for line numbers 596, 683, 742, 749, 750, 751, 

754, 755, 759, and 760; certificated in any 

category. 

Unsafe Condition 

(d) This AD was prompted by a report from 

the manufacturer that in production, during 

installation of certain attachment fasteners 

for the nacelle support fittings, only one 

washer was installed instead of two. We are 

issuing this AD to prevent inadequate 

fastener clamp-up, which could result in 

cracking of the fastener holes, cracking along 

the lower wing skin panels, fuel leaking from 

the wing fuel tanks onto the engines, and 

possible 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. 

Inspection/Measurement and Related 

Investigative and Corrective Actions 

(f) At the applicable time specified in 

paragraph (f)(1) or (f)(2) of this AD: Inspect/ 

measure the length of certain attachment 

fasteners between the lower wing skin panels 

and the nacelle support fittings. Do the 

inspection/measurement, and all applicable 

related investigative and corrective actions, 

in accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 737–

57–1275, Revision 1, dated August 18, 2005, 

except as provided by paragraph (g) of this 

AD. 

(1) For airplanes modified by 

Supplemental Type Certificate (STC) 

ST00830SE as of the effective date of this AD: 

Prior to the accumulation of 25,000 total 

flight hours or 25,000 total flight cycles, 

whichever is first. 

(2) For airplanes not modified by STC 

ST00830SE as of the effective date of this AD: 

Prior to the accumulation of 30,000 total 

flight hours or 30,000 total flight cycles, 

whichever is first. 

(g) If accomplishing a corrective action as 

required by paragraph (f) of this AD, and the 

service bulletin specifies to contact Boeing 

for repair information: Before further flight, 

do the repair using a method approved in 

accordance with paragraph (i) of this AD. 

Actions Accomplished According to 

Previous Issue of Service Bulletin 

(h) Actions accomplished before the 

effective date of this AD in accordance with 

Boeing Service Bulletin 737–57–1275, dated 

September 4, 2003, are considered acceptable 

for compliance with the corresponding action 

specified in 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 using 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. 

(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 Service Bulletin 

737–57–1275, Revision 1, dated August 18, 

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 

November 10, 2005. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 05–23056 Filed 11–22–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–23087; Directorate 

Identifier 2005–NM–225–AD; Amendment 

39–14386; AD 2005–24–06] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A318–100, A319–100, A320–200, A321–

100, and A321–200 Series Airplanes, 

and Model A320–111 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for all 

Airbus Model A318–100, A319–100, 

A320–200, A321–100, and A321–200 

series airplanes, and Model A320–111 

airplanes. This AD requires an 

inspection to determine whether certain 

braking and steering control units 

(BSCUs) are installed or have ever been 

installed. For airplanes on which certain 

BSCUs are installed or have ever been 

installed, this AD requires an inspection 

of the nose landing gear (NLG) upper 

support and corrective action if 

necessary, and a check of the NLG strut 

inflation pressure and an adjustment if 

necessary. For some of these airplanes, 

this AD also requires a revision to the 

aircraft flight manual to incorporate an 

operating procedure to recover normal 

steering in the event of a steering 

failure. This AD results from a report of 

an incident where an airplane landed 

with the NLG turned 90 degrees from 

centerline. We are issuing this AD to 

prevent landings with the NLG turned 

90 degrees from centerline, which could 

result in reduced controllability of the 

airplane. 

DATES: This AD becomes effective 

November 30, 2005. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of November 30, 2005. 

70716 Federal Register / Vol. 70, No. 225 / Wednesday, November 23, 2005 / Rules and Regulations 

We must receive comments on this 

AD by January 23, 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 Airbus, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France, 

for service information identified in this 

AD. 

FOR FURTHER INFORMATION CONTACT: Tim 

Dulin, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–2141; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We have received a report that an 

Airbus Model A320 series airplane 

landed with the nose landing gear (NLG) 

turned 90 degrees from centerline. The 

airplane landed safely with no reported 

injuries, but the NLG tires were quickly 

deflated and torn apart, and both wheels 

were worn up to the wheel axle. A 

boroscopic inspection of the NLG shock 

absorber upper attachment area was 

carried out and indicated that the upper 

support was damaged, which was 

confirmed after the NLG was torn down. 

Two diagonally opposite lugs were 

found sheared-off and one additional 

lug found cracked. 

The cause of the NLG turning 90 

degrees has been determined to be a 

combination of two failures: a failure of 

the upper support lugs, which 

prevented the centering cams from 

keeping the NLG in the center position 

when the shock absorber was extended 

and the steering system was 

depressurized; and a failure of the 

braking and steering control unit 

(BSCU), which prevented the normal 

steering system from re-centering the 

NLG. The NLG upper support lugs 

failed due to cyclic loading of the antirotation device by a new pre-land 

steering check introduced with the 

BSCU standard enhanced 

manufacturing and maintainability 

(EMM) software logic, combined with 

high shock absorber pressure. The BSCU 

EMM failed due to the time it takes for 

the steering system to re-center the NLG 

on airplanes equipped with a steering 

system powered by the green hydraulic 

system. Airplanes with the steering 

system supplied by the yellow 

hydraulic system are capable of recentering the nose landing gear even 

with broken upper support lugs. 

Relevant Service Information 

Airbus has issued Technical Note 

957.1901/05, dated October 18, 2005, 

which describes procedures for 

performing a boroscope inspection of 

the NLG upper support (backplate) to 

detect ruptured anti-rotation lugs and 

repair if necessary. 

Airbus has issued A318/A319/A320/ 

A321 aircraft maintenance manual 

(AMM) Temporary Revision (TR) 12–

001, dated November 13, 2005. The TR 

revises the data for Airbus A318/A319/ 

A320/A321 AMM, Chapter 12, Subject 

12–14–32, Revision 52, dated August 1, 

2005, which describes procedures for 

checking the NLG strut inflation 

pressure and adjusting as applicable. 

U.S. Type Certification of the Airplane 

These airplane models are 

manufactured in France and are typecertificated 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. 

FAA’s Determination and Requirements 

of This AD 

We are issuing this AD to prevent 

landings with the NLG turned 90 

degrees from centerline, which could 

result in reduced controllability of the 

airplane. This AD requires an inspection 

to determine whether certain BSCUs are 

installed or have ever been installed. 

For airplanes on which certain BSCUs 

are installed or have ever been installed, 

this AD requires a check of the NLG 

strut inflation pressure and an 

adjustment if necessary; and a 

boroscope inspection of the NLG upper 

support (backplate) to detect ruptured 

anti-rotation lugs, and corrective action 

if necessary. We consider a boroscope 

inspection necessary because it is the 

most effective means to detect a 

ruptured anti-rotation lug. The 

corrective action includes replacing the 

NLG with a serviceable NLG if the lugs 

are completely ruptured or contacting 

the FAA to determine whether 

replacement or continuing inspection is 

necessary if any other damage is found. 

For some of these airplanes on which 

certain BSCUs are installed or have ever 

been installed, this AD also requires a 

revision to the aircraft flight manual to 

incorporate an operating procedure to 

recover normal steering in event of a 

steering failure (i.e. when a ‘‘L/G 

SHOCK ABSORBER FAULT’’ electronic 

centralized aircraft monitoring (ECAM) 

caution is triggered at any time in flight 

and the ‘‘WHEEL N/W STRG FAULT’’

or ‘‘WHEEL N.W. STEER FAULT’’

ECAM cautions appear after landing 

gear extension). 

We have worked in conjunction with 

the European Aviation Safety Authority 

(EASA) (which is the airworthiness 

authority for the European Union (EU) 

Member States) and the Direction 

Ge ́ne ́rale de l’Aviation Civile (DGAC) 

(which is the airworthiness authority for 

France) to develop appropriate actions 

that will address the identified unsafe 

condition. We have been advised that 

EASA and the DGAC are considering 

issuing airworthiness directives with 

requirements similar to the 

requirements of this AD. 

Further, although this AD requires a 

one-time boroscope inspection, EASA 

and the DGAC have indicated that they 

do not plan to require the one-time 

boroscope inspection in their initial 

airworthiness directive. Rather, they 

have indicated that they plan to include 

the boroscope inspection with a longer 

compliance time in a follow-on 

airworthiness directive. EASA and the 

DGAC are aware of this difference, as 

well as the possibility that this AD may 

be issued earlier than their 

airworthiness directives on this subject. 

Interim Action 

We consider this AD interim action. 

The investigation into why the nose 

wheels were turned 90 degrees from the 

runway centerline is ongoing. Once we 

have received any further results of the 

investigation, we may consider 

additional rulemaking. 

FAA’s Determination of the Effective 

Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD; therefore, providing notice and 

opportunity for public comment before 

the AD is issued is impracticable, and 

good cause exists to make this AD 

effective in less than 30 days. 

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; 

Federal Register / Vol. 70, No. 225 / Wednesday, November 23, 2005 / Rules and Regulations 70717 

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–2005–23087; Directorate Identifier 

2005–NM–225–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): 

2005–24–06 Airbus: Amendment 39–14386. 

Docket No. FAA–2005–23087; 

Directorate Identifier 2005–NM–225–AD. 

Effective Date 

(a) This AD becomes effective November 

30, 2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to all Airbus Model 

A318–111 and –112 airplanes; Model A319–

111, –112, –113, –114, –115, –131, –132, and 

–133 airplanes; Model A320–111, –211, –212, 

–214, –231, –232, and –233 airplanes; and 

Model A321–111, –112, –131, –211, and –231 

airplanes; certificated in any category. 

Unsafe Condition 

(d) This AD results from a report of an 

incident where an airplane landed with the 

nose landing gear (NLG) turned 90 degrees 

from centerline. We are issuing this AD to 

prevent landings with the NLG turned 90 

degrees from centerline, which could result 

in reduced controllability 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. 

Records Review 

(f) Within 5 days after the effective date of 

this AD, perform a records review to 

determine whether the airplane is equipped 

with or has ever been equipped with a 

braking and steering control unit (BSCU) part 

number (P/N) E21327001 (standard L4.1, 

Airbus Modification 26965) or P/N 

E21327003 (standard L4.5, Airbus 

Modification 33376). 

(g) For airplanes on which a records review 

required by paragraph (f) of this AD 

conclusively determines that the airplane is 

not and never has been equipped with BSCU 

P/N E21327001 or P/N E21327003, no further 

action is required by this AD. 

Airplane Flight Manual (AFM) Revision, 

Inspection, and Corrective Action 

(h) For airplanes that are not specified in 

paragraph (g) of this AD and which do not 

have Airbus Modification 31152 incorporated 

in production (i.e. applicable only to aircraft 

with steering powered by the green hydraulic 

system): Within 10 days after the effective 

date of this AD, revise the Limitation Section 

of the Airbus A318/319/320/321 Aircraft 

Flight Manual (AFM) to include the 

following information. This may be done by 

inserting a copy of this AD into the AFM: 

The ECAM message, in case of a nose wheel 

steering failure, will be worded as follows: 

—‘‘WHEEL N/W STRG FAULT’’ for aircraft 

with the FWC E3 and subsequent standards 

—‘‘WHEEL N.W. STEER FAULT’’ for aircraft 

with the FWC E2 Standard. 

• If the L/G SHOCK ABSORBER FAULT 

ECAM caution is triggered at any time in 

flight, and the WHEEL N/W STRG FAULT 

ECAM caution is triggered after the landing 

gear extension: 

• When all landing gear doors are 

indicated closed on ECAM WHEEL page, 

reset the BSCU: 

—A/SKID&N/W STRG—OFF THEN ON 

■ If the WHEEL N/W STRG FAULT ECAM 

caution is no longer displayed, this indicates 

a successful nose wheel re-centering and 

steering recovery. 

—Rearm the AUTO BRAKE, if necessary. 

• If the WHEEL N/W STRG FAULT ECAM 

caution remains displayed, this indicates that 

the nose wheel steering remains lost, and that 

the nose wheels are not centered. 

—During landing, delay nose wheel 

touchdown for as long as possible. 

—Refer to the ECAM STATUS. 

70718 Federal Register / Vol. 70, No. 225 / Wednesday, November 23, 2005 / Rules and Regulations 

• If the WHEEL N/W STRG FAULT ECAM 

caution appears, without the L/G SHOCK 

ABSORBER FAULT ECAM caution: 

—No specific crew action is requested by the 

WHEEL N/W STRG FAULT ECAM caution 

procedure. 

—Refer to the ECAM STATUS. 

Note 1: When a statement identical to that 

in paragraph (h) of this AD has been included 

in the general revisions of the AFM, the 

general revisions may be inserted into the 

AFM, and the copy of this AD may be 

removed from the AFM. 

(i) For airplanes that are not specified in 

paragraph (g) of this AD: At the times 

specified in paragraphs (i)(1) and (i)(2) of this 

AD, perform a boroscope inspection of the 

NLG upper support (backplate) to detect 

ruptured (completely broken) anti-rotation 

lugs, in accordance with Airbus Technical 

Note 957.1901/05, dated October 18, 2005; 

and check the NLG strut inflation pressure 

and adjust as applicable before further flight, 

according to a method approved by either the 

Manager, International Branch, ANM–116, 

Transport Airplane Directorate, FAA; or the 

Direction Ge ́ne ́rale de l’Aviation Civile 

(DGAC) (or its delegated agent). Chapter 12, 

Subject 12–14–32 of the Airbus A318/A319/ 

A320/A321 Aircraft Maintenance Manual 

(AMM), as revised by Airbus A318/A319/ 

A320/A321 AMM Temporary Revision (TR) 

12–001, dated November 13, 2005, is one 

approved method. 

(1) Within 100 flight cycles following an 

electronic centralized aircraft monitoring 

(ECAM) caution ‘‘L/G SHOCK ABSORBER 

FAULT’’ associated with at least one of the 

centralized fault display system (CFDS) 

messages listed in paragraphs (i)(1)(i), 

(i)(1)(ii), and (i)(1)(iii) of this AD. 

(i) ‘‘N L/G EXT PROX SNSR 24GA TGT 

POS.’’

(ii) ‘‘N L/G EXT PROX SNSR 25GA TGT 

POS.’’

(iii) ‘‘N L/G SHOCK ABSORBER FAULT 

2526GM.’’

(2) Within 90 days after the effective date 

of this AD unless accomplished previously in 

accordance with paragraph (i)(1) of this AD. 

(j) If any ruptured (completely broken) 

upper support anti-rotation lugs are found 

during the inspections required by paragraph 

(i) of this AD, before further flight, replace 

the NLG with a serviceable NLG according to 

a method approved by either the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or the DGAC (or 

its delegated agent). Chapter 32 of the Airbus 

A318/A319/A320/A321 AMM is one 

approved method. If any other damage to the 

upper support lugs is found, before further 

flight, check whether the NLG wheels can be 

turned by hand without the compression of 

the shock absorber (i.e., without climbing the 

centering cam with the aircraft NLG on jacks) 

and the nose wheel steering disconnected 

from the electrical box 5GC. If the wheels can 

be turned, before further flight, replace the 

NLG with a serviceable NLG according to a 

method approved by either the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or the DGAC (or 

its delegated agent). Chapter 32 of the Airbus 

A318/A319/A320/A321 AMM is one 

approved method. If the wheels cannot be 

turned, within 100 flight cycles accomplish 

corrective actions (which could include 

replacement or continuing inspections) in 

accordance with a method approved by the 

Manager, International Branch, ANM–116, 

Transport Airplane Directorate, FAA. 

Alternative Methods of Compliance 

(AMOCs) 

(k)(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 

(l) None. 

Material Incorporated by Reference 

(m) You must use Airbus Technical Note 

957.1901/05, dated October 18, 2005, to 

perform the actions that are required by this 

AD, unless the AD specifies otherwise. (The 

document number of the Airbus technical 

note is only specified on page 1 of the 

document.) 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 Airbus, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France, 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 16, 2005. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 05–23154 Filed 11–22–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–23085; Directorate 

Identifier 2005–SW–25–AD; Amendment 39–

14385; AD 2005–24–05] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Vertol Model 107–II Helicopters 

AGENCY: Federal Aviation 

Administration, DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: This amendment adopts a 

new airworthiness directive (AD) for 

Boeing Vertol (Boeing) Model 107–II 

helicopters. This action requires a visual 

and magnetic particle inspection of the 

quill shaft. This amendment is 

prompted by the discovery of cracks in 

a quill shaft during a routine inspection. 

The actions specified in this AD are 

intended to detect a fatigue crack in a 

quill shaft and prevent separation of the 

quill shaft between the aft transmission 

and the mix box assembly, loss of rotor 

synchronization, and subsequent loss of 

control of the helicopter. 

DATES: Effective December 8, 2005. 

Comments for inclusion in the Rules 

Docket must be received on or before 

January 23, 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; or 

• 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. 

You may get the service information 

identified in this AD from The Boeing 

Company, c/o Service Engineering, MC 

P01–10, P.O. Box 16858, Philadelphia, 

PA 19142–3227. 

Examining the Docket 

You may examine the docket that 

contains the AD, any comments, and 

other information on the Internet at 

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

Docket Management System (DMS) 

Docket Offices between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. The Docket Office 

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

the plaza level of the Department of 

Transportation Nassif Building at the 

street address stated in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after the DMS 

receives them. 

FOR FURTHER INFORMATION CONTACT: 

George Duckett, Aviation Safety 

Engineer, FAA, New York Aircraft