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 

58358 Federal Register / Vol. 70, No. 193 / Thursday, October 6, 2005 / Proposed Rules 

Order 12866, the Regulatory Flexibility 

Act, or DOT Regulatory Policies and 

Procedures (44 FR 11034, February 26, 

1979). 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Safety. 

The Withdrawal 

Accordingly, the notice of proposed 

rulemaking, Docket 97–NM–78–AD, 

published in the Federal Register on 

January 5, 1998 (63 FR 169), is 

withdrawn. 

Issued in Renton, Washington, on 

September 29, 2005. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 05–20076 Filed 10–5–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–22629; Directorate 

Identifier 2005–NM–089–AD] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 737–200, –300, –400, and –500 

Series 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 Boeing Model 737–200, –300, 

–400, and –500 series airplanes. This 

proposed AD would require a one-time 

inspection of frames between station 

360 and station 907 to determine if a 

subject support bracket for the air 

conditioning outlet extrusion is 

installed, and related repetitive 

investigative actions and repair if 

necessary. This proposed AD also 

provides an optional preventive 

modification that would end the 

repetitive investigative actions. This 

proposed AD would also require a onetime post-modification/repair 

inspection for cracking of each repaired/ 

modified frame. This proposed AD 

results from numerous reports 

indicating that frame cracks have been 

found at the attachment holes for 

support brackets for the air conditioning 

outlet extrusion. We are proposing this 

AD to detect and correct such cracking, 

which, if the cracking were to continue 

to grow, could result in a severed frame. 

A severed frame, combined with 

existing multi-site damage at the 

stringer 10 lap splice, could result in 

rapid decompression of the airplane. 

DATES: We must receive comments on 

this proposed AD by November 21, 

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 Boeing Commercial 

Airplanes, P.O. Box 3707, Seattle, 

Washington 98124–2207, for the service 

information identified in this proposed 

AD. 

FOR FURTHER INFORMATION CONTACT: Sue 

Lucier, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 917–6438; 

fax (425) 917–6590. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to submit any relevant 

written data, views, or arguments 

regarding this proposed AD. Include the 

docket number ‘‘FAA–2005–22629; 

Directorate Identifier 2005–NM–089–

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 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 

We have received numerous reports 

indicating that frame cracks have been 

found at the attachment holes for 

support brackets for the air conditioning 

outlet extrusion on Boeing Model 737–

200, –300, –400, and –500 series 

airplanes. The subject support brackets 

have a certain part number and are 

attached to the frame with two rivets. 

Subject support brackets may be 

installed on frames between station 360 

and station 907. Investigation has 

revealed that the frame cracks occur due 

to fatigue and grow in a circumferential 

direction. The circumferential growth of 

the cracks is not likely to lead to a 

severed frame; however, with continued 

fatigue cycling, a crack could potentially 

turn in a direction that would lead to a 

severed frame. Also, frame cracks have 

been found on multiple adjacent frames, 

and at the lower row of fasteners of the 

stringer 10 lap joint, which is 

susceptible to multi-site damage. 

Therefore, frame cracks at the 

attachment holes for the support bracket 

of the air conditioning outlet extrusion, 

if not corrected, could eventually lead to 

a severed frame, which, combined with 

existing multi-site damage at the 

stringer 10 lap splice, could result in 

rapid decompression of the airplane. 

Relevant Service Information 

We have reviewed Boeing Special 

Attention Service Bulletin 737–53–

1216, dated January 27, 2005. Part I of 

the service bulletin describes 

procedures for a general visual 

inspection to identify where subject 

support brackets (defined previously) 

may be installed on frames between 

station 360 and station 907. Part I of the