Federal Register / Vol. 70, No. 193 / Thursday, October 6, 2005 / Proposed Rules 58355 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–22627; Directorate 

Identifier 2005–NM–156–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier 

Model CL–600–1A11 (CL–600), CL–

600–2A12 (CL–601), and CL–600–2B16 

(CL–601–3A and CL–601–3R) Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to adopt a 

new airworthiness directive (AD) for 

certain Bombardier Model CL–600–

1A11 (CL–600), CL–600–2A12 (CL–601), 

and CL–600–2B16 (CL–601–3A and CL–

601–3R) airplanes. This proposed AD 

would require measuring to detect 

migration of the lower gimbal pin and 

inspecting for other discrepancies of the 

horizontal stabilizer trim actuator 

(HSTA). This proposed AD also would 

require replacing or modifying the 

HSTA, as applicable. This proposed AD 

results from reports of failure of the 

lower gimbal pin of the HSTA. We are 

proposing this AD to prevent migration 

of the lower gimbal pin of the HSTA, 

which could result in loss of the 

horizontal stabilizer and consequent 

loss of control of the airplane. 

DATES: We must receive comments on 

this proposed AD by November 7, 2005. 

ADDRESSES: Use one of the following 

addresses to submit comments on this 

proposed 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 Bombardier, Inc., Canadair, 

Aerospace Group, P.O. Box 6087, 

Station Centre-ville, Montreal, Quebec 

H3C 3G9, Canada, for service 

information identified in this proposed 

AD. 

FOR FURTHER INFORMATION CONTACT: 

Daniel Parrillo, Aerospace Engineer, 

Systems and Flight Test Branch, ANE–

172, FAA, New York Aircraft 

Certification Office, 1600 Stewart 

Avenue, suite 410, Westbury, New York 

11590; telephone (516) 228–7305; fax 

(516) 794–5531. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to submit any relevant 

written data, views, or arguments 

regarding this proposed AD. Send your 

comments to an address listed in the 

ADDRESSES section. Include the docket 

number ‘‘FAA–2005–22627; Directorate 

Identifier 2005–NM–156–AD’’ at the 

beginning of your comments. We 

specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

the proposed AD. We will consider all 

comments received by the closing date 

and may amend the proposed AD in 

light of those comments. 

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 proposed 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. 

Discussion 

Transport Canada Civil Aviation 

(TCCA), which is the airworthiness 

authority for Canada, notified us that an 

unsafe condition may exist on certain 

Bombardier Model CL–600–1A11 (CL–

600), CL–600–2A12 (CL–601), and CL–

600–2B16 (CL–601–3A and CL–601–3R) 

airplanes. TCCA advises that there have 

been two failures of the lower gimbal 

pin of the horizontal stabilizer trim 

actuator (HSTA). In both cases, the 

broken pin was found during routine 

maintenance, and the broken pin had 

not migrated to the extent that operation 

of the HSTA was impaired. This 

condition, if not corrected, could result 

in loss of the horizontal stabilizer and 

consequent loss of control of the 

airplane. 

Relevant Service Information 

Bombardier has issued these service 

bulletins, both dated January 31, 2005: 

• Bombardier Service Bulletin 600–

0720 (for Model CL–600–1A11 (CL–600) 

airplanes). 

• Bombardier Service Bulletin 601–

0555 (for Bombardier Model CL–600–

2A12 (CL–601), and CL–600–2B16 (CL–

601–3A and CL–601–3R) airplanes). 

These service bulletins describe 

procedures for a one-time ‘‘special 

check’’ of the HSTA (which the service 

bulletins also refer to as the ‘‘pitch trim 

actuator’’) for migration of the lower 

gimbal pin, by measuring the clearance 

between the yoke and the lower side of 

the gimbal pin head, and for other 

discrepancies. Discrepancies are defined 

in a certain chapter of the airplane 

maintenance manual (which is 

referenced in the service bulletins), and 

include, but are not limited to, improper 

engagement of the lower gimbal pin 

retainers, loose or missing fasteners for 

the pin retainers, or other damage. If the 

gimbal pin has migrated or any 

discrepancy is found, the service 

bulletin specifies replacing the HSTA 

with a new or serviceable, modified 

HSTA, and reporting the findings to the 

manufacturer. If the gimbal pin has not 

migrated and no discrepancy is found, 

the service bulletin specifies modifying 

the HSTA by installing the gimbal pin 

kit (which involves installing additional 

pin retainer brackets and re-identifying 

the HSTA) or replacing the HSTA with 

a new or serviceable, modified HSTA. 

Accomplishing the actions specified 

in the service information is intended to 

adequately address the unsafe 

condition. TCCA mandated the service 

information and issued Canadian 

airworthiness directive CF–2005–20, 

dated June 23, 2005, to ensure the 

continued airworthiness of these 

airplanes in Canada. 

The Bombardier service bulletins refer 

to Goodrich Service Bulletin 21207–

00X–27–05, dated January 31, 2005, as 

an additional source of service 

information for doing the modification 

of the HSTA. 

58356 Federal Register / Vol. 70, No. 193 / Thursday, October 6, 2005 / Proposed Rules 

FAA’s Determination and Requirements 

of the Proposed AD 

These airplane models are 

manufactured in Canada and are 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, TCCA has 

kept the FAA informed of the situation 

described above. We have examined 

TCCA’s findings, evaluated all pertinent 

information, and determined that we 

need to issue an AD for airplanes of this 

type design that are certificated for 

operation in the United States. 

Therefore, we are proposing this AD, 

which would require accomplishing the 

actions specified in the service 

information described previously. The 

proposed AD would also require 

sending the inspection results to the 

manufacturer if the gimbal pin is found 

migrated. These inspection reports will 

help to determine the extent of migrated 

gimbal pins within the affected fleet. 

(While TCCA has received reports of 

broken lower gimbal pins, there have 

been no reports of migrated pins.) 

However, if migrated pins are found 

during the inspections that would be 

required by this proposed AD, this may 

indicate that further action is warranted. 

Clarification of Inspection Terminology 

The Canadian airworthiness directive 

and Bombardier service bulletins 

specify performing a ‘‘special check’’ of 

the HSTA for migration of the lower 

gimbal pin, by measuring the clearance 

between the yoke and the lower side of 

the gimbal pin head. The Bombardier 

service bulletins also specify to look for 

damage during this special check. For 

clarification, in this proposed AD, we 

refer to this check as a measurement (of 

the clearance between the yoke and the 

lower side of the gimbal pin head on the 

HSTA) to detect migration of the lower 

gimbal pin of the HSTA, and a detailed 

inspection for other discrepancies of the 

HSTA. We have included a note 

defining ‘‘detailed inspection.’’

Costs of Compliance 

This proposed AD would affect about 

269 airplanes of U.S. registry. The 

proposed measurement/inspection and 

modification would take about 5 work 

hours per airplane, at an average labor 

rate of $65 per work hour. Required 

parts would cost about $462 per 

airplane. Based on these figures, the 

estimated cost of the proposed AD for 

U.S. operators is $211,703, or $787 per 

airplane. 

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 

proposed AD would not have federalism 

implications under Executive Order 

13132. This proposed AD would not 

have a substantial direct effect on the 

States, on the relationship between the 

national Government and the States, or 

on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that the proposed regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

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

3. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this proposed 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, Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

2. The Federal Aviation 

Administration (FAA) amends § 39.13 

by adding the following new 

airworthiness directive (AD): 

Bombardier, Inc. (Formerly Canadair): 

Docket No. FAA–2005–22627; 

Directorate Identifier 2005–NM–156–AD. 

Comments Due Date 

(a) The FAA must receive comments on 

this AD action by November 7, 2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to the Bombardier 

airplanes identified in Table 1 of this AD, 

certificated in any category. 

TABLE 1.—APPLICABILITY

Bombardier airplane models Serial Nos. 

CL–600–1A11 (CL–600) ........................................................................... 1004 through 1085 inclusive. 

CL–600–2A12 (CL–601) ........................................................................... 3001 through 3066 inclusive. 

CL–600–2B16 (CL–601–3A and CL–601–3R) ......................................... 5001 through 5194 inclusive. 

Unsafe Condition 

(d) This AD results from reports of failure 

of the lower gimbal pin of the horizontal 

stabilizer trim actuator (HSTA). We are 

issuing this AD to prevent migration of the 

lower gimbal pin of the HSTA, which could 

result in loss of the horizontal stabilizer and 

consequent loss of control 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. 

Service Bulletin Reference 

(f) The term ‘‘service bulletin,’’ as used in 

this AD, means the Accomplishment 

Federal Register / Vol. 70, No. 193 / Thursday, October 6, 2005 / Proposed Rules 58357 

Instructions of the service bulletins identified 

in paragraphs (f)(1) and (f)(2) of this AD, as 

applicable. 

(1) For Model CL–600–1A11 (CL–600) 

airplanes: Bombardier Service Bulletin 600–

0720, dated January 31, 2005. 

(2) For Bombardier Model CL–600–2A12 

(CL–601), and CL–600–2B16 (CL–601–3A 

and CL–601–3R) airplanes: Bombardier 

Service Bulletin 601–0555, dated January 31, 

2005. 

Note 1: The Bombardier service bulletins 

identified in paragraphs (f)(1) and (f)(2) of 

this AD refer to Goodrich Service Bulletin 

21207–00X–27–05, dated January 31, 2005, 

as an additional source of service information 

for doing the modification of the HSTA. 

Measurement and Modification or 

Replacement 

(g) Within 600 flight hours or 16 months 

after the effective date of this AD, whichever 

is first: Measure the clearance between the 

yoke and the lower side of the gimbal pin 

head on the HSTA to detect migration of the 

lower gimbal pin of the HSTA, and do a 

detailed inspection to detect discrepancies of 

the HSTA, in accordance with the service 

bulletin. 

(1) If the lower gimbal pin has not migrated 

and no discrepancy is found: Modify the 

HSTA by installing the gimbal pin kit, or 

replace the existing HSTA with a new or 

serviceable, modified HSTA, in accordance 

with the service bulletin. 

(2) If the lower gimbal pin has migrated or 

any discrepancy is found: Before further 

flight, replace the HSTA with a new or 

serviceable, modified HSTA, in accordance 

with the service bulletin. 

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 

lenses, etc., may be necessary. Surface 

cleaning and elaborate procedures may be 

required.’’

Reporting 

(h) If any gimbal pin is found migrated: 

Submit a report of the findings (migrated 

pins only) of the measurement and 

inspections required by paragraph (g) of this 

AD to Bombardier, Attention Dept. Customer 

Support Program Office (CSPO), fax (514) 

855’8798. Submit the report at the applicable 

time specified in paragraph (h)(1) or (h)(2) of 

this AD. The report must include the airplane 

serial number, the HSTA part number and 

serial number, the results of the inspection, 

and the action taken. Submitting the Service 

Bulletin Feedback Form of the applicable 

service bulletin is an acceptable means of 

complying with this requirement. Under the 

provisions of the Paperwork Reduction Act of 

1980 (44 U.S.C. 3501 et seq.), the Office of 

Management and Budget (OMB) has 

approved the information collection 

requirements contained in this AD and has 

assigned OMB Control Number 2120–0056. 

(1) If the measurement was done after the 

effective date of this AD: Submit the report 

within 30 days after the inspection. 

(2) If the measurement was done prior to 

the effective date of this AD: Submit the 

report within 30 days after the effective date 

of this AD. 

Parts Installation 

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

person may install an HSTA on any airplane 

unless the actions required by paragraph (g) 

of this AD are accomplished on it. 

Alternative Methods of Compliance 

(AMOCs) 

(j)(1) The Manager, New York Aircraft 

Certification Office, 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 

(k) Canadian airworthiness directive CF–

2005–20, dated June 23, 2005, also addresses 

the subject of this AD. 

Issued in Renton, Washington, on 

September 28, 2005. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 05–20065 Filed 10–5–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 97–NM–78–AD] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 777 Series Airplanes Equipped 

With Pratt & Whitney Engines and 

Used in Extended Range Twin-Engine 

Operations (ETOPS) 

AGENCY: Federal Aviation 

Administration, DOT. 

ACTION: Proposed rule; withdrawal. 

SUMMARY: This action withdraws a 

notice of proposed rulemaking (NPRM) 

that proposed a new airworthiness 

directive (AD), applicable to certain 

Boeing Model 777 series airplanes 

equipped with Pratt & Whitney engines. 

That action would have required 

replacement of the integrated drive 

generator (IDG) and the backup 

generator with a new IDG and a new 

backup generator. Since the issuance of 

the NPRM, the Federal Aviation 

Administration (FAA) has received new 

data that indicate that all affected 

airplanes worldwide have the proper 

parts installed and all spares are 

accounted for, and that the identified 

unsafe condition (loss of electrical 

power) cannot occur for the reasons 

specified by the NPRM. Accordingly, 

the proposed rule is withdrawn. 

FOR FURTHER INFORMATION CONTACT: 

Tony Castillos, Aerospace Engineer, 

Systems and Equipment Branch, ANM–

130S, FAA, Seattle Aircraft Certification 

Office; 1601 Lind Avenue, SW., Renton, 

Washington 98055–4056; telephone 

(425) 227–2864; fax (425) 227–1181. 

SUPPLEMENTARY INFORMATION: A 

proposal to amend part 39 of the Federal 

Aviation Regulations (14 CFR part 39) to 

add a new airworthiness directive (AD), 

applicable to certain Boeing Model 777 

series airplanes equipped with Pratt & 

Whitney engines, was published in the 

Federal Register as a Notice of Proposed 

Rulemaking (NPRM) on January 5, 1998 

(63 FR 169). The proposed rule would 

have required replacement of the 

integrated drive generator (IDG) and the 

backup generator with a new IDG and a 

new backup generator. That action was 

prompted by reports of IDG shaft failure 

resulting from design problems in the 

hydraulic and mechanical systems of 

the generator, and by reports of backup 

generator failure resulting from the 

failure of the oil pressure switch. The 

proposed actions were intended to 

prevent continued degradation of the 

power system, and consequent loss of 

electrical power. 

Actions That Occurred Since the NPRM 

Was Issued 

Since the issuance of that NPRM, the 

FAA has received and confirmed reports 

indicating that all affected airplanes 

worldwide have the proper parts 

installed and that all spares are 

accounted for. 

FAA’s Conclusions 

Upon further consideration, the FAA 

has determined that the unsafe 

condition identified in the NPRM (loss 

of electrical power) can no longer occur 

because of the reasons given in the 

NPRM. Accordingly, the proposed rule 

is hereby withdrawn. 

Withdrawal of this NPRM constitutes 

only such action, and does not preclude 

the agency from issuing another action 

in the future, nor does it commit the 

agency to any course of action in the 

future. 

Regulatory Impact 

Since this action only withdraws a 

notice of proposed rulemaking, it is 

neither a proposed nor a final rule and 

therefore is not covered under Executive