Federal Register / Vol. 72, No. 60 / Thursday, March 29, 2007 / Proposed Rules 14721 

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. 

Inspections 

(f) At the later of the times specified in 

paragraphs (f)(1) and (f)(2) of this AD: Do the 

initial inspections specified in Table 1 of this 

AD in accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–30A2080, Revision 2, dated September 

14, 2006. Correct any discrepancy before 

further flight in accordance with the service 

bulletin. Repeat the inspections at the 

applicable time specified in Table 1 of this 

AD. 

(1) Within 18 calendar months since the 

date of issuance of the original standard 

airworthiness certificate or within 18 

calendar months since the date of issuance of 

the original export certificate of 

airworthiness. 

(2) Within 90 calendar days after the 

effective date of this AD. 

TABLE 1.—INSPECTIONS

Do a general visual inspection of the forward 

and aft cargo compartments, as applicable, 

for—

And repeat the inspection at intervals not to 

exceed— Until—

Foreign object debris (FOD) or contamination 

on, near, or around the potable water supply 

and gray water drain lines.

600 flight hours ................................................ The heater tape replacement required by 

paragraph (g) of this AD is done. 

Indications of heat damage, exposed foam insulation, or missing or damaged protective 

tape of all heater tape on the potable water 

supply and gray water drain lines.

1,800 flight hours ............................................. The heater tape replacement required by 

paragraph (g) of this AD is done. 

Terminating Action 

(g) At the applicable time specified in 

Table 2 of this AD: Replace the heater tape 

on the potable water supply and gray water 

drain lines of the forward and aft cargo 

compartments, as applicable, with Adel 

Wiggins ribbon heaters. Do the actions in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–30A2080, Revision 2, dated September 

14, 2006. This replacement terminates the 

requirements of paragraph (f) of this AD. 

TABLE 2.—COMPLIANCE TIME FOR TERMINATING ACTION

For airplanes on which the heater tape has— Replace the heater tape at the later of—

(1) Not been replaced before the effective date 

of this AD in accordance with Boeing Alert 

Service Bulletin 747–30A2079, dated December 12, 2002; Revision 1, dated October 16, 

2003; or Revision 2, dated December 16, 

2004.

Within 42 months since the date of issuance 

of the original standard airworthiness certificate or the date of issuance of the original 

export certificate of airworthiness, whichever occurs first.

24 months after the effective date of this AD. 

(2) Been replaced before the effective date of 

this AD in accordance with Boeing Alert 

Service Bulletin 747–30A2079, dated December 12, 2002; Revision 1, dated October 16, 

2003; or Revision 2, dated December 16, 

2004.

Within 42 months after the heater tape was 

replaced.

24 months after the effective date of this AD. 

Provisions for Previous Accomplished Work 

(h) Actions done before the effective date 

of this AD in accordance with Boeing Alert 

Service Bulletin 747–30A2080—either the 

original version dated December 16, 2004, or 

Revision 1, dated August 18, 2005—are 

acceptable for compliance with the 

corresponding requirements of this AD; 

except, for Group 2, Configuration 2 and 

Configuration 3 airplanes, as defined in 

Revision 2 of the service bulletin, additional 

work is required in the forward cargo 

compartment, as specified in Parts 1, 2, and 

3 of the service bulletin and required by this 

AD. 

Alternative Methods of Compliance 

(AMOCs) 

(i)(1) The Manager, Seattle 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 § 39.19 on any airplane to 

which the AMOC applies, notify the 

appropriate principal inspector in the FAA 

Flight Standards Certificate Holding District 

Office. 

Issued in Renton, Washington, on March 

20, 2007. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E7–5667 Filed 3–28–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–27713; Directorate 

Identifier 2006–NM–240–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier 

Model DHC–8–100, DHC–8–200, and 

DHC–8–300 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 Bombardier Model DHC–8–100, 

DHC–8–200, and DHC–8–300 series 

airplanes. This proposed AD would 


pwalker on PROD1PC71 with PROPOSALS
14722 Federal Register / Vol. 72, No. 60 / Thursday, March 29, 2007 / Proposed Rules 

require, for certain airplanes, 

modification of the upper bearing of the 

main landing gear (MLG) shock strut. 

This proposed AD would also require, 

for certain airplanes, revising the DHC–

8 Maintenance Program Manual to 

include the MLG shock strut servicing 

task. This proposed AD results from 

reports of over-extension of the MLG 

shock strut piston, which allows the 

torque links to go over-center and rest 

on the piston. We are proposing this AD 

to prevent loss in shock absorption 

during touchdown and failure of the 

shock strut housing, which could result 

in a subsequent loss of directional 

control. 

DATES: We must receive comments on 

this proposed AD by April 30, 2007. 

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., Bombardier 

Regional Aircraft Division, 123 Garratt 

Boulevard, Downsview, Ontario M3K 

1Y5, Canada, for service information 

identified in this proposed AD. 

FOR FURTHER INFORMATION CONTACT: 

Mazdak Hobbi, Aerospace Engineer, 

Airframe and Propulsion Branch, ANE–

171, FAA, New York Aircraft 

Certification Office, 1600 Stewart 

Avenue, suite 410, Westbury, New York 

11590; telephone (516) 228–7330; 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–2007–27713; Directorate 

Identifier 2006–NM–240–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 DHC–8–100, DHC–

8–200, and DHC–8–300 series airplanes. 

TCCA advises that there have been six 

cases reported in which the main 

landing gear (MLG) shock strut piston 

over-extended, allowing the torque links 

to go over-center and rest on the piston. 

Investigation has revealed that overextension of the shock strut resulted 

from damage to the upper bearing and 

seal carrier, caused by a loss of internal 

damping. 

Over-extension of the MLG shock 

strut piston, if not corrected, could 

result in loss in shock absorption during 

touchdown and failure of the shock 

strut housing, which could result in a 

subsequent loss of directional control. 

Relevant Service Information 

Bombardier has issued Service 

Bulletin 8–32–144, Revision ‘A,’ dated 

April 29, 2002, including MessierDowty Service Bulletin M–DT SBDHC8–

32–82, Revision 1, dated July 5, 2001 

(for Model DHC–8–311, –314, and –315 

airplanes). The service bulletin 

describes procedures for modifying the 

upper bearing in each MLG. The 

modification includes an inspection of 

the two halves of the upper bearing for 

wear and damage, the removal of the 

needle roller from the upper bearing, an 

inspection of the cylinder bore for 

damage and wear, and corrective action 

if necessary. The corrective action 

includes replacing the upper bearing 

with a new bearing and contacting the 

parts manufacturer if damage or wear 

that exceeds the maximum diameter is 

found on the cylinder bore. 

Bombardier has issued the following 

de Havilland Dash 8 maintenance task 

cards to the applicable Bombardier 

DHC–8 Maintenance Program Manual 

(Program Support Manuals 1–8–7, 1–

82–7, and 1–83–7). These tasks describe 

procedures for servicing the MLG shock 

struts: 

• Dash 8 Series 100 Maintenance 

Task Card 3210/15, dated June 22, 2005; 

• Dash 8 Series 200 Maintenance 

Task Card 3210/15, dated June 22, 2005; 

and 

• Dash 8 Series 300 Maintenance 

Task Card 3210/15, dated November 29, 

2005. 

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–2006–14, 

effective July 21, 2006, to ensure the 

continued airworthiness of these 

airplanes in Canada. 

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, for certain 

airplanes, accomplishing the actions 

specified in the service bulletin 

described previously, and, for certain 

airplanes, revising the applicable DCH–

8 Maintenance Program Manual to 

include the MLG shock strut servicing 

Task 3210/15, except as discussed 


pwalker on PROD1PC71 with PROPOSALS
Federal Register / Vol. 72, No. 60 / Thursday, March 29, 2007 / Proposed Rules 14723 

under ‘‘Difference Between the 

Proposed AD and the Service Bulletin.’’

Difference Between the Proposed AD 

and the Service Bulletin 

The service bulletin specifies to 

contact the manufacturer for 

instructions on how to repair certain 

conditions, but this proposed AD would 

require repairing those conditions using 

a method that we or TCCA (or its 

delegated agent) approve. In light of the 

type of repair that would be required to 

address the unsafe condition, and 

consistent with existing bilateral 

airworthiness agreements, we have 

determined that, for this proposed AD, 

a repair we or TCCA approve would be 

acceptable for compliance with this 

proposed AD. 

Costs of Compliance 

The following table provides the 

estimated costs for U.S. operators to 

comply with this proposed AD. 

ESTIMATED COSTS

Action Work hours 

Average 

labor rate 

per hour 

Parts Cost per 

airplane 

Number of U.S.- 

registered 

airplanes 

Fleet cost 

Modification ........................................................ 4 $80 $274 $594 Up to 135 ......... Up to $80,190. 

Manual Revision ................................................ 1 80 0 80 135 ................... $10,800. 

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 de Havilland, 

Inc.): Docket No. FAA–2007–27713; 

Directorate Identifier 2006–NM–240–AD. 

Comments Due Date 

(a) The FAA must receive comments on 

this AD action by April 30, 2007. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Bombardier Model 

DHC–8–101, –102, –103, –106, –201, –202, 

–301, –311, –314, and –315 airplanes, 

certificated in any category; serial numbers 

003 through 618 inclusive. 

Unsafe Condition 

(d) This AD results from reports of overextension of the main landing gear (MLG) 

shock strut piston, which allows the torque 

links to go over-center and rest on the piston. 

We are issuing this AD to prevent loss in 

shock absorption during touchdown and 

failure of the shock strut housing, which 

could result in a subsequent loss of 

directional control. 

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. 

Modification of the Upper Bearing 

(f) For Model DHC–8–311, –314, and –315 

airplanes, serial numbers 202 through 516 

inclusive, with MLG shock struts having any 

serial number DCL3501/90 through 

DCL3768/97 inclusive installed: Within 

3,000 flight hours after the effective date of 

this AD, modify the upper bearing in each 

MLG (including doing inspections of the 

upper bearing and cylinder bore for wear and 

damage, and doing all applicable corrective 

actions) in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 8–32–144, Revision ‘A,’

dated April 29, 2002, including MessierDowty Service Bulletin M–DT SBDHC8–32–

82, Revision 1, dated July 5, 2001, except if 

wear exceeds the maximum diameter 

specified in the service bulletin for the 

cylinder bore or if damage is found on the 

cylinder bore, before further flight, repair 

using a method approved by either the 

Manager, International Branch, ANM–116, 

Transport Airplane Directorate, FAA; or 

Transport Canada Civil Aviation (TCCA) (or 

its delegated agent). Do all applicable 

corrective actions before further flight. 

Revision of the Maintenance Program 

Manual 

(g) For Model DHC–8–101, –102, –103, 

–106, –201, –202, –301, –311, –314, and –315 

airplanes, serial numbers 003 through 614 

inclusive: Within 30 days after the effective 

date of this AD, revise Part 1 of the 

applicable DHC–8 Maintenance Program 

Manual by incorporating the applicable MLG 

shock strut servicing Task 3210/15 specified 

in Table 1 of this AD. 

Note 1: This may be done by inserting 

copies of the applicable task into the 

applicable maintenance program manual. 

When these tasks have been included in the 

general revisions of the applicable 


pwalker on PROD1PC71 with PROPOSALS
14724 Federal Register / Vol. 72, No. 60 / Thursday, March 29, 2007 / Proposed Rules 

maintenance program manual, the general 

revisions may be inserted in the applicable 

maintenance program manual and the copy 

of the task may be removed from the 

maintenance program manual. 

TABLE 1.—TASKS

Task— Dated—

To the 

program 

support manual 

(PSM)—

For model—

Dash 8 Series 100 Maintenance Task 

Card 3210/15.

June 22, 2005 ........................................ 1–8–7 DHC–8–100 Series Airplanes. 

Dash 8 Series 200 Maintenance Task 

Card 3210/15.

June 22, 2005 ........................................ 1–82–7 DHC–8–200 Series Airplanes. 

Dash 8 Series 300 Maintenance Task 

Card 3210/15.

November 29, 2005 ............................... 1–83–7 DHC–8–300 Series Airplanes. 

Parts Installation 

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

person may install a part identified in 

paragraphs (h)(1) and (h)(2) of this AD, as a 

replacement during the repair or overhaul of 

any shock strut assembly, on any airplane. 

(1) Upper bearing, part number 10130–3 or 

10130–551. 

(2) Damper ring, part number 10129–3 or 

10129–551. 

(i) After the effective date of this AD, only 

the parts identified in paragraphs (i)(1) and 

(i)(2) of this AD may be installed on any 

airplane as replacement upper bearings and 

damper rings during the repair or overhaul of 

any shock strut assembly, except as provided 

by paragraph (j) of this AD. 

(1) Upper bearing, part number 10130–5. 

(2) Damper ring, part number 10129–5 or 

10129–533. 

(j) After the effective date of this AD, only 

MLGs with a reworked, oversize cylinder 

bore (part number identified in the 

applicable component maintenance manual 

(CMM)) that have parts identified in 

paragraphs (j)(1), (j)(2), and (j)(3) of this AD 

used in accordance with the applicable CMM 

may be installed on any airplane. 

(1) Upper bearing, part number CRS85–

167–11. 

(2) Damper ring, part number CRS85–167–

31 or CRS85–167–33. 

(3) Seal carrier, part number CRS85–167–

21. 

Credit for Actions Done Using Previous 

Service Information 

(k) Modifications accomplished before the 

effective date of this AD in accordance with 

Bombardier Service Bulletin 8–32–144, dated 

August 10, 1998, including Messier-Dowty 

Service Bulletin M–DT SBDCH8–32–82, 

dated March 9, 1998, are considered 

acceptable for compliance with the 

corresponding actions specified in this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(l)(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 § 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 

(m) Canadian airworthiness directive CF–

2006–14, effective July 21, 2006, also 

addresses the subject of this AD. 

Issued in Renton, Washington, on March 

20, 2007. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E7–5668 Filed 3–28–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–26966; Directorate 

Identifier 99–NE–01–AD] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

Corporation AE 3007A and AE 3007C 

Series Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to 

supersede an existing airworthiness 

directive (AD) for Rolls-Royce 

Corporation (RRC) AE 3007A and AE 

3007C series turbofan engines. That AD 

currently prohibits any flight following 

a ground engine start where the engine 

oil temperature is below 32 °F (0 °C), 

unless certain preflight operational 

procedures are followed. This proposed 

AD would also require those actions, 

and would also require a terminating 

action. This proposed AD would 

supersede the compliance requirements 

of AD 99–02–51 and all related 

alternative methods of compliance 

(AMOCs). This proposed AD results 

from design improvements to 

components in the accessory gearbox air 

turbine starter mounting pad. We are 

proposing this AD to prevent an inflight engine shutdown due to loss of 

engine oil from the starter shaft seal. 

DATES: We must receive any comments 

on this proposed AD by May 29, 2007. 

ADDRESSES: Use one of the following 

addresses to comment 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–

0001. 

• 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 Rolls-Royce Corporation, P.O. 

Box 420, Indianapolis, IN 46206; 

telephone (317) 230–3774; fax (317) 

230–8084; e-mail: 

indy.pubs.services@rolls-royce.com, to 

get the service information identified in 

this proposed AD. 

FOR FURTHER INFORMATION CONTACT: Kyri 

Zaroyiannis, Aerospace Engineer, 

Chicago Aircraft Certification Office, 

Small Airplane Directorate, FAA, 2300 

E. Devon Ave., Des Plaines, IL 60018; 

telephone (847) 294–7836; fax (847) 

294–7834. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments 

regarding this proposal. Send your 

comments to an address listed under 

ADDRESSES. Include ‘‘Docket No. FAA–


pwalker on PROD1PC71 with PROPOSALS