This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by

the Superintendent of Documents. Prices of

new books are listed in the first FEDERAL

REGISTER issue of each week.

Rules and Regulations Federal Register

65827 

Vol. 70, No. 210 

Tuesday, November 1, 2005 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 98–NM–300–AD; Amendment 

39–14355; AD 2005–22–11] 

RIN 2120–AA64 

Airworthiness Directives; Mitsubishi 

Model YS–11 Airplanes, and Model YS– 

11A–200, YS–11A–300, YS–11A–500, 

and YS–11A–600 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: This amendment adopts a 

new airworthiness directive (AD), 

applicable to certain Mitsubishi Model 

YS–11 airplanes, and Model YS–11A– 

200, YS–11A–300, YS–11A–500, and 

YS–11A–600 series airplanes. This AD 

requires repetitive removal of the 

spinner; repetitive detailed inspections 

of the propeller hub to detect fatigue 

cracking; and replacement of a propeller 

hub with a new propeller hub, if 

necessary. This action is necessary to 

detect and correct fatigue cracking of the 

propeller hub, which could cause the 

loss of the propeller. This action is 

intended to address the identified 

unsafe condition. 

DATES: Effective December 6, 2005. 

ADDRESSES: The service information 

referenced in this AD may be obtained 

from Nihon Aeroplane Manufacturing, 

Toranomon Daiichi, Kotohire-Cho, 

Shiba, Minato-Ku, Tokyo, Japan. This 

information may be examined at the 

Federal Aviation Administration (FAA), 

Transport Airplane Directorate, Rules 

Docket, 1601 Lind Avenue, SW., 

Renton, Washington; or at the FAA, Los 

Angeles Aircraft Certification Office, 

3960 Paramount Boulevard, Lakewood, 

California. 

FOR FURTHER INFORMATION CONTACT: 

Brent Bandley, Project Engineer, 

Continuing Operational Safety, ANM– 

100L, FAA, Los Angeles Aircraft 

Certification Office, 3960 Paramount 

Boulevard, Lakewood, California 

90712–4137; telephone (562) 627–5237; 

fax (562) 627–5210. 

SUPPLEMENTARY INFORMATION: A 

proposal to amend part 39 of the Federal 

Aviation Regulations (14 CFR part 39) to 

include an airworthiness directive (AD) 

that is applicable to all Mitsubishi 

Model YS–11 and YS–11A series 

airplanes was published in the Federal 

Register on August 31, 1999 (64 FR 

47442). That action proposed to require 

repetitive removal of the spinner; 

repetitive detailed visual inspections of 

the propeller hub to detect fatigue 

cracking; and replacement of a propeller 

hub with a new propeller hub, if 

necessary. 

Comments 

Interested persons have been afforded 

an opportunity to participate in the 

making of this amendment. Due 

consideration has been given to the 

comments received. 

Request To Include Only Airplanes 

With Incorrectly Inspected Propeller 

Hubs 

Two commenters, the airplane 

manufacturer and the Japan Civil 

Aviation Bureau (JCAB), which is the 

airworthiness authority for Japan, 

request that we limit the airplanes 

affected by the notice of proposed 

rulemaking (NPRM) to those that have 

propeller hubs that were inspected 

incorrectly. The commenters explain 

that, after we issued the NPRM, which 

applies to all Mitsubishi Model YS–11 

and YS–11A series airplanes, the JCAB 

found some discrepancies in procedures 

that an overhauler used when 

inspecting the hub. The JCAB revised its 

airworthiness directive and issued 

Japanese airworthiness directive TCD– 

4667A–98, dated March 18, 1998, to 

apply only to the hubs that were 

inspected incorrectly. The commenters 

request that we incorporate the list of 

applicable propellers into the final rule. 

We infer that the commenters are also 

stating that hubs that were correctly 

inspected are not subject to the stated 

unsafe condition. We agree with the 

commenters; only propeller hubs that 

were incorrectly inspected are subject to 

the unsafe condition. Therefore, the 

final rule should be applicable only to 

airplanes on which these incorrectly 

inspected propeller hubs are installed. 

The Japanese airworthiness directive 

identifies the affected propellers by 

serial number. We have revised the 

summary and applicability of the final 

rule to reflect this change and to include 

only those serial numbers. 

Request To Exclude Airplanes With 

Strengthened Propeller Hubs 

The same commenters request that we 

exclude from the applicability any 

affected airplane that has a propeller 

hub that was strengthened in 

accordance with Dowty Rotol Service 

Bulletin 61–921, dated April 24, 1980, 

or later version approved by the JCAB. 

The commenters state that strengthened 

hubs do not require a repetitive visual 

inspection. The Japanese airworthiness 

directive excludes from its applicability 

all airplanes that have strengthened 

hubs; however, JCAB also notes in its 

comment that there have been two 

reports of cracks in strengthened hubs. 

In addition, the commenters request that 

we incorporate the actions in this 

service bulletin into the requirements of 

the final rule. 

We do not agree with the commenters. 

The JCAB noted that there have been 

two reports of cracks found in hubs that 

have been modified in accordance with 

the Dowty Rotol service bulletin. We 

have determined that propellers with 

the strengthened hubs do have a 

potential unsafe cracking condition 

because it has been reported that 

strengthened hubs have also cracked. 

The strengthened hubs should not be 

excluded from the applicability and 

inspection requirements of the final 

rule. We have not changed the final rule 

in this regard. 

Explanation of Further Changes to the 

Final Rule 

We have revised the applicability to 

reflect the model designations as 

published in the most recent type 

certificate data sheets. 

We have changed paragraph (a)(2) of 

the final rule to refer to the repair 

procedure to follow if any crack is 

detected in a hub. 

We have changed references to a 

‘‘detailed visual inspection’’ to 

‘‘detailed inspection.’’ We have 

included the definition for a detailed 

inspection in a note in the final rule. 

65828 Federal Register / Vol. 70, No. 210 / Tuesday, November 1, 2005 / Rules and Regulations 

Although the Japanese airworthiness 

directive referenced in this AD specifies 

to submit certain information to the 

JCAB, this AD does not include that 

requirement. 

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. 

Conclusion 

After careful review of the available 

data, including the comments noted 

above, the FAA has determined that air 

safety and the public interest require the 

adoption of the rule with the changes 

described previously. The FAA has 

determined that these changes will 

neither increase the economic burden 

on any operator nor increase the scope 

of the AD. 

Changes to 14 CFR Part 39/Effect on the 

AD 

On July 10, 2002, the FAA issued a 

new version of 14 CFR part 39 (67 FR 

47997, July 22, 2002), which governs the 

FAA’s airworthiness directives system. 

The regulation now includes material 

that relates to altered products, special 

flight permits, and alternative methods 

of compliance. However, for clarity and 

consistency in this final rule, we have 

retained the language of the NPRM 

regarding that material. 

Cost Impact 

Since we issued the NPRM, we have 

determined that 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 

32 work hours per airplane to 

accomplish the inspection, and that the 

average labor rate is $65 per work hour. 

Based on these figures, the estimated 

cost of the AD would be $2,080 per 

airplane. 

The cost impact figure discussed 

above is based on assumptions that no 

operator has yet accomplished any of 

the requirements of this AD action, and 

that no operator would accomplish 

those actions in the future if this AD 

were not adopted. The cost impact 

figures discussed in AD rulemaking 

actions represent only the time 

necessary to perform the specific actions 

actually required by the AD. These 

figures typically do not include 

incidental costs, such as the time 

required to gain access and close up, 

planning time, or time necessitated by 

other administrative actions. 

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 Impact 

The regulations adopted herein 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. Therefore, it is 

determined that this final rule does not 

have federalism implications under 

Executive Order 13132. 

For the reasons discussed above, I 

certify that this action (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. A final evaluation has 

been prepared for this action and it is 

contained in the Rules Docket. A copy 

of it may be obtained from the Rules 

Docket at the location provided under 

the caption ADDRESSES. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Safety. 

Adoption of the Amendment 

■ Accordingly, pursuant to the authority 

delegated to me by the Administrator, 

the Federal Aviation Administration 

amends part 39 of the Federal Aviation 

Regulations (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. Section 39.13 is amended by adding 

the following new airworthiness 

directive: 

2005–22–11 Mitsubishi Heavy Industries, 

LTD.: Amendment 39–14355. Docket 98–

NM–300–AD. 

Applicability: Model YS–11 airplanes, and 

Model YS–11A–200, YS–11A–300, YS–11A–

500, and YS–11A–600 series airplanes, 

certificated in any category; having propeller 

hubs with the following serial numbers: 

CHE942, DRG1/74, DRG7/68, DRG8/68, 

DRG13/70, DRG14/71, DRG31/68, DRG33/70, 

DRG34/68, DRG35/68, DRG48/69, DRG53/69, 

DRG65/78, DRG72/69, DRG73/68, DRG75/69, 

DRG83/65, DRG87/68, DRG105/67, DRG126/ 

70, DRG128/68, DRG130/70, DRG132/68, 

DRG132/70, DRG134/68, DRG137/67, 

DRG150/69, DRG154/65, DRG161/70, 

DRG179/68, DRG180/68, DRG194/63, 

DRG208/67, DRG231/70, DRG238/65, 

DRG275/68, DRG281/68, DRG284/64, 

DRG300/63, DRG302/67, DRG308/64, 

DRG308/66, DRG486/67, and DRG551/67. 

Note 1: This AD applies to each airplane 

identified in the preceding applicability 

provision, regardless of whether it has been 

modified, altered, or repaired in the area 

subject to the requirements of this AD. For 

airplanes that have been modified, altered, or 

repaired so that the performance of the 

requirements of this AD is affected, the 

owner/operator must request approval for an 

alternative method of compliance in 

accordance with paragraph (b) of this AD. 

The request should include an assessment of 

the effect of the modification, alteration, or 

repair on the unsafe condition addressed by 

this AD; and, if the unsafe condition has not 

been eliminated, the request should include 

specific proposed actions to address it. 

Compliance: Required as indicated, unless 

accomplished previously. 

To detect and correct fatigue cracking of 

the propeller hub, which could cause the loss 

of the propeller, accomplish the following: 

Inspection and Replacement 

(a) Within 25 flight hours or 30 days after 

the effective date of this AD, whichever 

occurs first, remove the spinner and perform 

a detailed inspection for cracking of the 

propeller hub in the crack area shown in 

Figure 1 of this AD. 

Note 2: 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 

Federal Register / Vol. 70, No. 210 / Tuesday, November 1, 2005 / Rules and Regulations 65829 

lenses, etc., may be necessary. Surface 

cleaning and elaborate procedures may be 

required.’’

(1) If no crack is found, repeat the actions 

required by paragraph (a) of this AD 

thereafter at intervals not to exceed 25 flight 

hours. 

(2) If any crack is detected, prior to further 

flight, replace the hub with a new hub 

according to a method approved by either the 

Manager, Los Angeles Aircraft Certification 

Office (ACO), FAA; or the Japan Civil 

Aviation Bureau (JCAB) (or its delegated 

agent). Chapter 61 of the Nihon Aeroplane 

Manufacturing Company YS–11 and YS–11A 

Aircraft Maintenance Manuals is one 

approved method. Repeat the actions 

required by paragraph (a) of this AD 

thereafter at intervals not to exceed 25 flight 

hours. 

BILLING CODE 4910–13–P 

65830 Federal Register / Vol. 70, No. 210 / Tuesday, November 1, 2005 / Rules and Regulations 


ER01NO05.001</GPH>
Federal Register / Vol. 70, No. 210 / Tuesday, November 1, 2005 / Rules and Regulations 65831 

BILLING CODE 4910–13–C 


ER01NO05.002</GPH>
65832 Federal Register / Vol. 70, No. 210 / Tuesday, November 1, 2005 / Rules and Regulations 

Alternative Methods of Compliance 

(b)(1) An alternative method of compliance 

or adjustment of the compliance time that 

provides an acceptable level of safety may be 

used if approved by the Manager, Los 

Angeles ACO. Operators shall submit their 

requests through an appropriate FAA 

Principal Maintenance Inspector, who may 

add comments and then send it to the 

Manager, Los Angeles ACO. 

(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. 

Note 3: Information concerning the 

existence of approved alternative methods of 

compliance with this AD, if any, may be 

obtained from the Los Angeles ACO. 

Special Flight Permits 

(c) Special flight permits may be issued for 

non-revenue bearing flights with essential 

crew only in accordance with sections 21.197 

and 21.199 of the Federal Aviation 

Regulations (14 CFR 21.197 and 21.199) to 

operate the airplane to a location where the 

requirements of this AD can be 

accomplished. 

Note 4: The subject of this AD is addressed 

in Japanese airworthiness directive TCD–

4667A–98, dated March 18, 1998. 

Incorporation by Reference 

(d) None. 

Effective Date 

(e) This amendment becomes effective on 

December 6, 2005. 

Issued in Renton, Washington, on October 

20, 2005. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 05–21543 Filed 10–31–05; 8:45 am] 

BILLING CODE 4910–13–C 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2005–20322; Airspace 

Docket No. 05–ANM–1] 

RIN 2120–AA66 

Establishment and Revision of Area 

Navigation (RNAV) Routes; Western 

United States 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; correction. 

SUMMARY: This action corrects errors in 

the legal description of Area Navigation 

(RNAV) Routes listed in a final rule 

published in the Federal Register on 

October 14, 2005 (70 FR 59990), 

Airspace Docket No. 05–ANM–1. 

EFFECTIVE DATE: 0901 UTC, December 

22, 2005. 

FOR FURTHER INFORMATION CONTACT: Ken 

McElroy, Airspace and Rules, Office of 

System Operations Airspace and AIM, 

Federal Aviation Administration, 800 

Independence Avenue, SW., 

Washington, DC 20591; telephone: (202) 

267–8783. 

SUPPLEMENTARY INFORMATION: 

History 

On October 14, 2005, a final rule was 

published in the Federal Register (70 

FR 59990), Airspace Docket No. 05–

ANM–1. This rule established three 

RNAV routes (Q–15, Q–2, Q–4, and 

revised Q–13) in the Western United 

States. In all four routes, points that 

were listed in the route descriptions as 

‘‘waypoint’’ (WP) are actually existing 

published navigation ‘‘fixes.’’ Therefore, 

the descriptions are corrected by 

removing ‘‘WP’’ and substituting ‘‘Fix.’’

In addition, the title for Q–13 was 

reversed. This action corrects those 

errors. 

Correction to Final Rule 

■ Accordingly, pursuant to the authority 

delegated to me, the legal description 

for Q–13, Q–15, Q–2 and Q–4, as 

published in the Federal Register on 

October 14, 2005 (70 FR 59990), 

Airspace Docket No. 05–ANM–1, are 

corrected as follows: 

PART 71—[AMENDED] 

§ 71.1 [Amended] 

* * * * * 

Q–13 PRFUM to PAWLI [Corrected] 

PRFUM .......................................................... Fix .................................................................. (Lat. 35°30′24′′ N., long. 113°56′35′′ W.) 

CENIT ............................................................ WP ................................................................. (Lat. 36°41′02′′ N., long. 116°26′31′′ W.) 

TUMBE .......................................................... WP ................................................................. (Lat. 36°48′20′′ N., long. 116°40′03′′ W.) 

TACUS ........................................................... WP ................................................................. (Lat. 37°05′16′′ N., long. 116°54′12′′ W.) 

WODIN .......................................................... WP ................................................................. (Lat. 37°19′20′′ N., long. 117°05′25′′ W.) 

LEAHI ............................................................ WP ................................................................. (Lat. 37°28′58′′ N., long. 117°14′57′′ W.) 

LOMIA ........................................................... WP ................................................................. (Lat. 39°13′12′′ N., long. 119°06′23′′ W.) 

RUFUS ........................................................... WP ................................................................. (Lat. 41°26′00′′ N., long. 120°00′00′′ W.) 

PAWLI ........................................................... WP ................................................................. (Lat. 43°10′48′′ N., long. 120°55′50′′ W.) 

* * * * * * * 

Q–15 CHILY to LOMIA [Corrected] 

CHILY ............................................................ Fix .................................................................. (Lat. 34°42′49′′ N., long. 112°45′42′′ W.) 

DOVEE ........................................................... Fix .................................................................. (Lat. 35°26′51′′ N., long. 114°48′01′′ W.) 

BIKKR ............................................................ WP ................................................................. (Lat. 36°34′00′′ N., long. 116°45′00′′ W.) 

DOBNE ........................................................... WP ................................................................. (Lat. 37°14′23′′ N., long. 117°15′04′′ W.) 

RUSME .......................................................... WP ................................................................. (Lat. 37°29′39′′ N., long. 117°31′12′′ W.) 

LOMIA ........................................................... WP ................................................................. (Lat. 39°13′12′′ N., long. 119°06′23′′ W.) 

* * * * * * * 

Q–2 BOILE to EWM [Corrected] 

BOILE ............................................................. Fix .................................................................. (Lat. 34°25′21′′ N., long. 118°01′33′′ W.) 

HEDVI ............................................................ WP ................................................................. (Lat. 33°32′23′′ N., long. 114°28′14′′ W.) 

HOBOL .......................................................... WP ................................................................. (Lat. 33°11′30′′ N., long. 112°20′00′′ W.) 

ITUCO ............................................................ WP ................................................................. (Lat. 32°26′30′′ N., long. 109°46′26′′ W.) 

EWM .............................................................. VORTAC ........................................................ (Lat. 31°57′06′′ N., long. 106°16′21′′ W.) 

* * * * * * * 

Q–4 BOILE to ELP [Corrected] 

BOILE ............................................................. Fix .................................................................. (Lat. 34°25′21′′ N., long. 118°01′33′′ W.) 

HEDVI ............................................................ WP ................................................................. (Lat. 33°32′23′′ N., long. 114°28′14′′ W.) 

SCOLE ............................................................ Fix .................................................................. (Lat. 33°27′46′′ N., long. 114°04′54′′ W.)