9662 Federal Register / Vol. 72, No. 42 / Monday, March 5, 2007 / Rules and Regulations 

Actions Compliance Procedures 

(2) Replace the old engine mount attaching 

hardware by doing the following:.

(i) Remove and discard the upper left and 

upper right engine mount attaching hardware; 

(ii) Cut out and remove the upholstery and 

insulation material to allow full metal-tometal contact of the fuselage tubular 

frame to the firewall; and 

(iii) Install the new upper left and upper 

right engine mount attaching hardware 

part kits 

Within the next 100 hours time-in-service 

(TIS) after April 9, 2007 (the effective date 

of this AD).

Follow Mooney Airplane Company, Inc. Service Bulletin M20–292A, dated December 

22, 2006. 

(3) If you do the actions of paragraph (e)(2) of 

this AD before the compliance time specified 

for the action in paragraph (e)(1) of this AD, 

it terminates the requirement for the action in 

paragraph (e)(1) of this AD.

As of April 9, 2007 (the effective date of this 

AD).

Follow Mooney Airplane Company, Inc. Service Bulletin M20–292A, dated December 

22, 2006. 

(f) Compliance will be acceptable if the 

above actions are accomplished by following 

the procedures described in Mooney 

Airplane Company, Inc. Service Bulletin 

M20–292, dated September 22, 2006. You 

may take ‘‘unless already done’’ credit, and 

no further action per this AD is necessary. 

Alternative Methods of Compliance 

(AMOCs) 

(g) The Manager, Fort Worth Airplane 

Certification Office, FAA, ATTN: Andrew 

McAnaul, Aerospace Engineer, ASW–150 

(c/o MIDO–43), 10100 Reunion Place, Suite 

650, San Antonio, Texas 78216; telephone: 

(210) 308–3365; fax: (210) 308–3370, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. 

Related Information 

(h) None. 

Material Incorporated by Reference 

(i) You must use Mooney Airplane 

Company, Inc. Service Bulletin M20–292A, 

dated December 22, 2006, to do the actions 

required by this AD, unless the AD specifies 

otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact the Mooney Airplane 

Company, Inc., 165 Al Mooney Road North, 

Kerrville, TX 78028, telephone: 830–896–

6000, or go to: http://www.mooney.com/ 

images/pdfs/sb-pdf/m20-292a.pdf. 

(3) You may review copies at the FAA, 

Central Region, Office of the Regional 

Counsel, 901 Locust, Kansas City, Missouri 

64106; or at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at NARA, call 202–741–6030, or go 

to: http://www.archives.gov/federal_register/ 

code_of_federal_regulations/ibr_

locations.html. 

Issued in Kansas City, Missouri, on 

February 21, 2007. 

Kim Smith, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. E7–3575 Filed 3–2–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–23871; Directorate 

Identifier 2006–NE–01–AD; Amendment 39–

14975; AD 2007–05–14] 

RIN 2120–AA64 

Airworthiness Directives; General 

Electric Company (GE) CF6–80C2 

Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for GE 

CF6–80C2 series turbofan engines. This 

AD requires replacing certain installed 

part number (P/N) and serial number 

(SN) cast titanium weld-repaired 

forward engine mount platforms and 

cast titanium forward mount yokes, 

with a forged titanium or a non-welded 

cast titanium part. This AD results from 

the discovery of cracks, in a weldrepaired area on a forward engine 

mount platform and a forward engine 

mount yoke, found during a fluorescent 

penetrant inspection (FPI). These parts 

were weld-repaired during manufacture. 

We are issuing this AD to prevent cracks 

in the forward engine mount platform 

and forward engine mount yoke that 

could result in possible separation of 

the engine from the airplane. 

DATES: This AD becomes effective April 

9, 2007. 

ADDRESSES: You can get the service 

information identified in this AD from 

General Electric Company via Lockheed 

Martin Technology Services, 10525 

Chester Road, Suite C, Cincinnati, Ohio 

45215, telephone (513) 672–8400, fax 

(513) 672–8422. 

You may examine the AD docket on 

the Internet at http://dms.dot.gov or in 

Room PL–401 on the plaza level of the 

Nassif Building, 400 Seventh Street, 

SW., Washington, DC. 

FOR FURTHER INFORMATION CONTACT: 

James Lawrence, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

and Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; telephone (781) 238–7176; fax 

(781) 238–7199. 

SUPPLEMENTARY INFORMATION: The FAA 

proposed to amend 14 CFR part 39 with 

a proposed AD. The proposed AD 

applies to GE CF6–80C2 series turbofan 

engines. We published the proposed AD 

in the Federal Register on December 13, 

2006 (71 FR 74873). That action 

proposed to require replacing certain 

installed part number (P/N) and serial 

number (SN) cast titanium weldrepaired forward engine mount 

platforms and cast titanium forward 

mount yokes, with a forged titanium or 

a non-welded cast titanium part. 

Examining the AD Docket 

You may examine the docket that 

contains the AD, any comments 

received, and any final disposition in 

person at the Docket Management 

Facility 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 ADDRESSES. 


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Federal Register / Vol. 72, No. 42 / Monday, March 5, 2007 / Rules and Regulations 9663 

Comments will be available in the AD 

docket shortly after the DMS receives 

them. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comments received. 

Add Airbus A310 and MD–11 Airplanes 

to the Applicability 

Commenters from Lufthansa Technik, 

KLM Royal Dutch Airlines, Airbus and 

Alitalia state that this AD is also 

applicable to the engines installed in the 

A310 and MD–11 airplanes. We agree. 

We inadvertently omitted the Airbus 

A310 and MD–11 airplanes from the 

Applicability section of the proposed 

rule. These airplanes are included in the 

Applicability section of the AD. 

Reference GE Service Bulletins 

Commenters from Lufthansa Technik, 

KLM Royal Dutch Airlines, Airbus and 

Alitalia also state that because the AD 

mandates requirements contained in GE 

Service Bulletins, CF6–80C2 S/B 72–

1206 and CF6–80C2 S/B 72–1207, the 

FAA should reference the service 

bulletins in the final rule. We agree. The 

service bulletins’ accomplishment 

instructions contain information such as 

applicable Aircraft Maintenance Manual 

sections that would clarify requirements 

of the AD. A reference to the service 

bulletins is included in the Related 

Information Section of the AD. 

Location of Weld Repair 

Representatives from Lufthansa 

Technik and KLM Royal Dutch Airlines 

note that paragraph (h) of the 

applicability section identifies a weld 

repair in a redundant area of the yoke, 

but Table 3 identifies the weld repair in 

a non-redundant area of the yoke. The 

FAA needs to correct this inconsistency 

in the final rule. We agree and have 

changed the heading of Table 3 to read, 

‘‘Weld-Repaired Forward Engine Mount 

Yokes Requiring Replacement That 

Have a Weld Repair in a Redundant 

Area of the Yoke.’’

Conclusion 

We have carefully reviewed the 

available data, including the comments 

received, and determined that air safety 

and the public interest require adopting 

the AD with the changes described 

previously. We have determined that 

these changes will neither increase the 

economic burden on any operator nor 

increase the scope of the AD. 

Costs of Compliance 

There are 25 engines in service that 

contain the substandard forward engine 

mount platforms and 59 engines in 

service that contain the substandard 

forward engine mount yokes. We 

estimate that this proposed AD would 

affect 84 CF6–80C2 engines installed on 

airplanes of U.S. registry. We estimate 

that it would take 34 work-hours per 

engine to replace the weld-repaired cast 

titanium forward engine mount 

platforms and the weld-repaired cast 

titanium forward engine mount yokes. 

The average labor rate is $80 per workhour. Required forward engine mount 

parts would cost about $12,168 per 

engine. Required forward engine mount 

yoke parts would cost about $39,560 per 

engine. Based on these figures, we 

estimate the total cost of the proposed 

AD to U.S. operators to be $2,866,720. 

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 this AD: 

(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. 

We prepared a summary of the costs 

to comply with this AD and placed it in 

the AD Docket. You may get a copy of 

this summary at the address listed 

under ADDRESSES. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Safety. 

Adoption of the Amendment 

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the Federal Aviation Administration 

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 FAA amends § 39.13 by adding 

the following new airworthiness 

directive: 

2007–05–14 General Electric Company: 

Amendment 39–14975. Docket No. 

FAA–2006–23871; Directorate Identifier 

2006–NE–01–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective April 9, 2007. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to the following 

General Electric Company (GE) turbofan 

engines with cast titanium assembly engine 

mount platforms part numbers (P/Ns) 

1292M13G06, 1301M28G08, 1459M70G07, 

and 1846M24G04 and cast titanium assembly 

engine mount yokes P/Ns 9383M43G14 and 

9383M43G16 installed. 

CF6–80C2A1 

CF6–80C2A2 

CF6–80C2A3 

CF6–80C2A5 

CF6–80C2A8 

CF6–80C2A5F 

CF6–80C2B1 

CF6–80C2B2 

CF6–80C2B4 

CF6–80C2B6 

CF6–80C2B1F 

CF6–80C2B2F 

CF6–80C2B4F 

CF6–80C2B5F 

CF6–80C2B6F 

CF6–80C2B6FA 

CF6–80C2B7F 

CF6–80C2B8F 

CF6–80C2D1F 

These engines are installed on, but not 

limited to, Boeing 747, Boeing 767, MD–11 

and Airbus A300–600 and A310 airplanes. 


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Unsafe Condition 

(d) This AD results from the discovery of 

cracks in a forward engine mount platform 

and a forward engine mount yoke found 

during fluorescent penetrant inspection (FPI). 

We are issuing this AD to prevent cracks in 

the forward engine mount platform and 

forward engine mount yoke that could result 

in possible separation of the engine from 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. 

P/N and SN Weld-Repaired Forward Engine 

Mount Platforms and Forward Engine Mount 

Yokes Requiring Replacement 

(f) Table 1 of this AD lists the P/Ns and 

serial numbers (SNs) of the weld-repaired 

forward engine mount platforms that have a 

weld repair in a non-redundant area of the 

mount and must be replaced. 

TABLE 1.—WELD-REPAIRED FORWARD

ENGINE MOUNT PLATFORMS REQUIRING REPLACEMENT THAT HAVE

A WELD REPAIR IN A NON-REDUNDANT AREA OF THE MOUNT

P/Ns SNs 

1292M13G06 or 

1846M24G04 

WACHH228 

WACHH254 

WACHH285 

WACHH290 

WACHH292 

WACHH295 

WACHH299 

WACHH384 

WACHH427 

WACHH440 

WACHH604 

1301M28G08 ..................... WACAR292 

WACAR354 

(g) Table 2 of this AD lists the P/Ns and 

SNs of the weld-repaired forward engine 

mount platforms that have a weld repair in 

a redundant area of the mount. Because it is 

impossible to detect whether the mount is 

operating on the redundant feature, each of 

these mounts must be replaced. The 

compliance time for mounts in this category 

can be longer than for the mounts listed in 

Table 1 of this AD. 

TABLE 2.—WELD-REPAIRED FORWARD

ENGINE MOUNT PLATFORMS REQUIRING REPLACEMENT THAT HAVE

A WELD REPAIR IN A REDUNDANT

AREA OF THE MOUNT

P/Ns SNs 

1292M13G06 or 

1846M24G04 

WACHH173 

WACHH189 

WACHH274 

WACHH278 

WACHH314 

WACHH325 

WACHH486 

TABLE 2.—WELD-REPAIRED FORWARD

ENGINE MOUNT PLATFORMS REQUIRING REPLACEMENT THAT HAVE

A WELD REPAIR IN A REDUNDANT

AREA OF THE MOUNT—Continued 

P/Ns SNs 

1301M28G08 ..................... WACAR294 

WACAR304 

WACAR353 

WACAR372 

1459M70G07 ..................... MTXT1282 

(h) Table 3 of this AD lists the P/Ns and 

SNs of the weld-repaired forward engine 

mount yokes that have a weld repair in a 

redundant area of the yoke. Because it is 

impossible to detect whether the mount yoke 

is operating on the redundant feature, each 

of these mount yokes must be replaced. The 

compliance time for mounts in this category 

can be longer than for the mounts listed in 

Table 1 of this AD. 

TABLE 3.—WELD-REPAIRED FORWARD

ENGINE MOUNT YOKES REQUIRING

REPLACEMENT THAT HAVE A WELD

REPAIR IN A REDUNDANT AREA OF

THE YOKE

P/Ns SNs 

9383M43G14 ..................... WACV0388 

WACV0394 

WACV0405 

WACV0406 

WACV0477 

WACV0498 

WACV0529 

WACV0556 

WACV0579 

WACV0581 

WACV0582 

WACV0600 

WACV0605 

WACV0617 

WACV0625 

WACV0627 

WACV0633 

WACV0645 

WACV0683 

WACV0703 

WACV0733 

WACV0737 

WACV0759 

WACV0775 

WACV0791 

WACV0799 

WACV0875 

WACV0883 

WACV0885 

WACV0909 

WACV1097 

WACV1615 

WACV1713 

WACV1753 

WACV1797 

WACV1867 

WACV1987 

WACV2131 

WACV2159 

WACV2185 

WACV2343 

TABLE 3.—WELD-REPAIRED FORWARD

ENGINE MOUNT YOKES REQUIRING

REPLACEMENT THAT HAVE A WELD

REPAIR IN A REDUNDANT AREA OF

THE YOKE—Continued 

P/Ns SNs 

WACV2511 

WACV2695 

WACV2707 

WACV2881 

WACV2899 

9383M43G16 ..................... WACV0511 

WACV0515 

WACV0518 

WACV0540 

WACV0542 

WACV0571 

WACV0689 

WACV0721 

WACV0727 

WACV0730 

WACV0786 

WACV0816 

WACV0954 

(i) GE advises that forward engine mount 

platform, P/Ns 1292M13G06 and 

1846M24G04, are the same, except that P/N 

1846M24G04 incorporates a previously 

approved field rework. This rework allows 

the thrust pin hole in the forward engine 

mount platform to be bored out to accept 

installation of an oversized thrust pin. GE 

cannot identify which SN goes with which P/ 

N, but all SNs are affected. 

Welded Cast Titanium Forward Engine 

Mount Platform and Forward Engine Mount 

Yoke Removal 

(j) If the P/N and SN of the forward engine 

mount platform listed in Table 1 and Table 

2 and the forward engine mount yoke listed 

in Table 3 of this AD are not installed on the 

engine, no further action is necessary. 

(k) If the P/N and SN of the forward engine 

mount platform listed in Table 1 of this AD 

is installed on the engine: 

(1) Remove the forward engine mount 

platform from the engine within 500 cycles 

or 6 months, after the effective date of this 

AD, whichever occurs first. 

(2) Information for removal of the forward 

engine mount platform from the engine can 

be found in the CF6–80C2 Engine Manual, 

72–00–01, Disassembly. 

(l) If the P/N and SN of the forward engine 

mount platform listed in Table 2 of this AD 

is installed on the engine: 

(1) Remove the forward engine mount 

platform at the next shop visit, or within 

4,800 cycles after the effective date of this 

AD, whichever occurs first. 

(2) Information for removal of the forward 

engine mount yoke can be found in the CF6–

80C2 Engine Manual, 72–00–01, 

Disassembly. 

(m) If the P/N and SN of the forward 

engine mount yoke listed in Table 3 of this 

AD is installed on the engine: 

(1) Remove the forward engine mount yoke 

at the next shop visit, or within 4,800 cycles 

after the effective date of this AD, whichever 

occurs first. 


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Federal Register / Vol. 72, No. 42 / Monday, March 5, 2007 / Rules and Regulations 9665 

(2) Information for removal of the forward 

engine mount yoke can be found in the CF6–

80C2 Engine Manual, 72–00–01, 

Disassembly. 

(n) Replace the affected forward engine 

mount platform and or the affected forward 

engine mount yoke with a non-weld-repaired 

cast titanium forward engine mount platform 

and or the forward engine mount yoke or a 

forged titanium forward engine mount 

platform or a forged titanium forward engine 

mount yoke. 

(o) Information for installing the forward 

engine mount platform and forward engine 

mount yoke can be found in the CF6–80C2 

Engine Manual, 72–00–01, Assembly. 

(p) Location of the forward engine mount 

platform and forward engine mount yoke and 

SN are illustrated in the following Figure 1. 

BILLING CODE 4910–13–P 

(q) After the effective date of this AD, do 

not install a weld-repaired, cast forward 

engine mount platform or a weld-repaired, 

cast forward engine mount yoke in any 

engine. 

Alternative Methods of Compliance 

(r) The Manager, Engine Certification 

Office, has the authority to approve 

alternative methods of compliance for this 

AD if requested using the procedures found 

in 14 CFR 39.19. 

Related Information 

(s) Contact James Lawrence, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine and Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; telephone (781) 238–7176; fax (781) 


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9666 Federal Register / Vol. 72, No. 42 / Monday, March 5, 2007 / Rules and Regulations 

238–7199 for more information about this 

AD. 

(t) General Electric Company Service 

Bulletins CF6–80C2 S/B 72–1206, dated 

December 23, 2005, and CF6–80C2 S/B 72–

1207, Revision 01, dated July 05, 2006, 

pertain to the subject of this AD. 

Issued in Burlington, Massachusetts, on 

February 27, 2007. 

Peter A. White, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 07–986 Filed 3–2–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–26378; Directorate 

Identifier 2006–NM–230–AD; Amendment 

39–14972; AD 2007–05–11] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier 

Model CL–600–2B16 (CL–604) 

Airplanes and Model CL–600–2B19 

(Regional Jet Series 100 & 440) 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is superseding two 

existing airworthiness directives (ADs), 

that apply to certain Bombardier Model 

CL–600–2B16 (CL–604) airplanes and 

Model CL–600–2B19 (Regional Jet 

Series 100 & 440) airplanes. These 

models may be referred to by their 

marketing designations as RJ100, RJ200, 

RJ440, CRJ100, CRJ200, CRJ440, and 

CL–65. One existing AD requires 

replacing the horizontal stabilizer trim 

control unit (HSTCU) with a new 

HSTCU. The other existing AD requires 

revising the airplane flight manual 

(AFM) to advise the flightcrew of 

procedures to follow in the event of 

stabilizer trim runaway, and in the 

event of MACH TRIM, STAB TRIM, and 

horizontal stabilizer trim malfunctions; 

and revising the AFM to require a 

review of the location of certain circuit 

breakers. That AD also requires doing a 

functional check of the stabilizer trim 

system and installing circuit breaker 

identification collars, and provides an 

optional terminating action. This new 

AD requires the previously optional 

terminating action and requires further 

revisions to the AFM. This AD also 

requires the removal of certain AFM 

revisions. This AD results from reports 

of trim problems including 

uncommanded trim, trim in the 

opposite direction to that selected, loss 

of trim position indication and, in one 

case, potential loss of trim disconnect 

capability. We are issuing this AD to 

prevent these events, which could result 

in conditions that vary from reduced 

controllability of the airplane to loss of 

control of the airplane. 

DATES: This AD becomes effective 

March 20, 2007. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of March 20, 2007. 

On November 14, 2006 (71 FR 63219, 

October 30, 2006), the Director of the 

Federal Register approved the 

incorporation by reference of certain 

other publications. 

On July 30, 1998 (63 FR 34574, June 

25, 1998), the Director of the Federal 

Register approved the incorporation by 

reference of a certain other publication. 

We must receive any comments on 

this AD by April 4, 2007. 

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 Bombardier, Inc., Canadair, 

Aerospace Group, P.O. Box 6087, 

Station Centre-ville, Montreal, Quebec 

H3C 3G9, Canada, for service 

information identified in this AD. 

You may examine the contents of the 

AD docket on the Internet at http:// 

dms.dot.gov, or in person at the Docket 

Management Facility, U.S. Department 

of Transportation, 400 Seventh Street, 

SW., Room PL–401, on the plaza level 

of the Nassif Building, Washington, DC. 

This docket number is FAA–2006–

26378; the directorate identifier for this 

docket is 2006–NM–230–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: 

Discussion 

On October 13, 2006, the FAA issued 

a supplemental notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that 

supersedes AD 2006–22–06, amendment 

39–14803 (71 FR 63219, October 30, 

2006). The existing AD applies to 

certain Bombardier Model CL–600–

2B16 (CL–604) airplanes and Model CL–

600–2B19 (Regional Jet Series 100 & 

440) airplanes. That supplemental 

NPRM was published in the Federal 

Register on December 28, 2006 (71 FR 

78096). That supplemental NPRM 

proposed to retain the requirements of 

AD 2006–22–06 and to require the 

previously optional terminating action 

(installation of a new horizontal 

stabilizer trim control unit (HSTCU)). 

That supplemental NPRM also proposed 

to require, for certain airplanes, reinserting the applicable temporary 

revisions of the Emergency and 

Abnormal Procedures sections of the 

airplane flight manual (AFM) under 

certain conditions. 

Actions Since Supplemental NPRM 

Was Issued 

Since we issued that supplemental 

NPRM, Bombardier has issued new 

temporary revisions (TRs) to the AFMs 

as described in a comment submitted by 

the National Transportation Safety 

Board (NTSB) (see ‘‘Request to Revise 

AFM Procedures’’ paragraph below). In 

the comment, the NTSB presents data to 

indicate that changes to the AFMs are 

necessary to address the identified 

unsafe condition. We have coordinated 

with Transport Canada Civil Aviation 

(TCCA) on this issue and concur that 

changes to the AFMs are necessary. In 

consideration of these new data, we 

have determined that the AFMs must be 

revised to include the new TRs within 

14 days after the effective date of this 

AD. 

The FAA finds that, with respect to 

this additional requirement, since a 

situation exists that requires immediate 

adoption of this requirement, notice and 

time for prior public comment hereon 

are impracticable, and good cause exists 

for making this amendment effective in 

less than 30 days. Therefore, this AD 

will include the requirements specified 

in the supplemental NPRM (except the 

proposed requirement to re-insert TRs to 

the AFMs), as well as the certain new 

requirements discussed below. The new 

requirements include revising the AFMs 

to include the new TRs. In addition, we 


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