Federal Register / Vol. 80, No. 50 / Monday, March 16, 2015 / Rules and Regulations 13483 

airworthy upper skin. Repeat the inspection 

of the longeron assembly at intervals not to 

exceed 50 hours TIS. 

(ii) If there is a crack, corrosion, or other 

damage in the longeron assembly, before 

further flight: 

(A) Repair the longeron assembly or 

replace it with an airworthy longeron 

assembly, part number (P/N) 206–031–314– 

237B, and reinstall the upper skin or replace 

it with an airworthy upper skin. 

(B) Install three external strap doublers in 

accordance with Part III, paragraphs 5 

through10 of Bell Helicopter Alert Service 

Bulletin 407–11–95, Revision C, dated April 

20, 2012 (ASB). 

(C) Repeat the inspection of the longeron 

assembly at intervals not to exceed 50 hours 

TIS. 

(2) If there is no crack in the upper skin, 

within 10 hours TIS, visually inspect the 

longeron assembly using a 10X or higher 

power magnifying glass for a crack, 

corrosion, or other damage. 

(i) If there is a crack, corrosion, or other 

damage in the longeron assembly, before 

further flight: 

(A) Repair the longeron assembly or 

replace it with an airworthy longeron 

assembly, P/N 206–031–314–237B. 

(B) Install three external strap doublers in 

accordance with Part III, paragraphs 5 

through 10 of the ASB. 

(C) Repeat the inspection of the upper skin 

and longeron assembly at intervals not to 

exceed 50 hours TIS. 

(ii) If there are no cracks, corrosion, or 

other damage in the longeron assembly, 

repeat the inspection of the upper skin and 

longeron assembly at intervals not to exceed 

50 hours TIS. 

(3) Replacing the longeron assembly with 

longeron assembly, P/N 206–031–314–237B, 

and installing three external strap doublers 

constitutes terminating action for this AD. 

(4) If there is no crack in the upper skin 

and there is no crack, corrosion, or other 

damage in the longeron assembly, you may 

install three external strap doublers in 

accordance with Part III, paragraphs 5 

through 10 of the ASB. This option extends 

the recurring 50 hours TIS inspection 

interval to 150 hours TIS. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Sharon Miles, 

Aviation Safety Engineer, Regulations and 

Policy Group, Rotorcraft Directorate, FAA, 

2601 Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

sharon.y.miles@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office, before 

operating any aircraft complying with this 

AD through an AMOC. 

(g) Additional Information 

The subject of this AD is addressed in 

Transport Canada Civil Aviation (TCCA) AD 

No. CF–2011–42, dated November 9, 2011. 

You may view the TCCA AD on the Internet 

at http://www.regulations.gov in Docket No. 

FAA–2014–0070. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 5313, Fuselage Main, Longeron/

Stringer. 

(i) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Bell Helicopter Alert Service Bulletin 

407–11–95, Revision C, dated April 20, 2012. 

(ii) Reserved. 

(3) For BHTC service information 

identified in this AD, contact Bell Helicopter 

Textron Canada Limited, 12,800 Rue de 

l’Avenir, Mirabel, Quebec J7J1R4; telephone 

(450) 437–2862 or (800) 363–8023; fax (450) 

433–0272; or at 

http://www.bellcustomer .com/files/. 

(4) You may view this service information 

at FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham Blvd., 

Room 663, Fort Worth, Texas 76137. For 

information on the availability of this 

material at the FAA, call (817) 222–5110. 

(5) You may view this service information 

that is incorporated by reference 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/cfr/ibrlocations.html. 

Issued in Fort Worth, Texas, on March 3, 

2015. 

Bruce E. Cain, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–05571 Filed 3–13–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0491; Directorate 

Identifier 2015–NM–019–AD; Amendment 

39–18117; AD 2015–05–07] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2015–02– 

06 for certain Bombardier, Inc. Model 

CL–600–2B16 (CL–604 Variant) 

airplanes. AD 2015–02–06 required a 

revision to the airplane flight manual, a 

revision to the maintenance or 

inspection program, as applicable, and 

replacement of horizontal stabilizer trim 

actuators (HSTAs) having certain part 

numbers. This new AD continues to 

require those actions and corrects 

certain typographical errors. This AD 

was prompted by the discovery of three 

typographical errors in AD 2015–02–06. 

We are issuing this AD to detect and 

correct loose spur gear bolts on the 

HSTA, which, if combined with the 

failure of the primary load path, could 

lead to failure of the HSTA and 

subsequent loss of the airplane. 

DATES: This AD becomes effective 

March 16, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of March 6, 2015 (80 FR 5017, 

January 30, 2015). 

We must receive comments on this 

AD by April 30, 2015 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC, between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. 

• For service information identified 

in this AD, contact Bombardier, Inc., 

400 Coˆte Vertu Road West, Dorval, 

Que ́bec H4S 1Y9, Canada; telephone 

514–855–5000; fax 514–855–7401; email 

thd.crj@aero.bombardier.com; Internet 

http://www.bombardier.com. You may 

view this referenced service information 

at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., 

Renton, WA. For information on the 

availability of this material at the FAA, 

call 425–227–1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

0491; or in person at the Docket 

Operations office between 9 a.m. and 

5 p.m., Monday through Friday, except 


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13484 Federal Register / Vol. 80, No. 50 / Monday, March 16, 2015 / Rules and Regulations 

Federal holidays. The AD docket 

contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (telephone 

800–647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Ricardo Garcia, Aerospace Engineer, 

Airframe and Propulsion Branch, ANE– 

171, FAA, New York Aircraft 

Certification Office, 1600 Stewart 

Avenue, Suite 410, Westbury, NY 

11590; telephone 516–228–7331; fax 

516–794–5531. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On January 11, 2015, we issued AD 

2015–02–06, Amendment 39–18073 (80 

FR 5017, January 30, 2015). AD 2015– 

02–06 applied to certain Bombardier, 

Inc. Model CL–600–2B16 (CL–604 

Variant) airplanes. AD 2015–02–06 was 

prompted by reports of loose, broken, or 

backed-out spur gear bolts on the HSTA. 

AD 2015–02–06 required a revision to 

the airplane flight manual, a revision to 

the maintenance or inspection program, 

as applicable, and replacement of 

HSTAs having certain part numbers. We 

issued AD 2015–02–06 to detect and 

correct loose spur gear bolts on the 

HSTA, which, if combined with the 

failure of the primary load path, could 

lead to failure of the HSTA and 

subsequent loss of the airplane. 

Since we issued AD 2015–02–06, 

Amendment 39–18073 (80 FR 5017, 

January 30, 2015), three typographical 

errors were discovered in AD 2015–02– 

06. 

As published, a digit was missing 

from the engineer’s phone number in 

the FOR FURTHER INFORMATION CONTACT

section of the preamble of AD 2015–02– 

06, Amendment 39–18073 (80 FR 5017, 

January 30, 2015). The correct phone 

number is ‘‘516–228–7331.’’ 

As published, the AD number of AD 

2015–02–06, Amendment 39–18073 (80 

FR 5017, January 30, 2015), appears as 

‘‘2014–02–06’’ in the Product 

Identification line of the regulatory text 

of the AD. The correct AD number is 

‘‘2015–02–06.’’ The AD number is 

referenced correctly throughout the 

remainder of that document. 

As published, a vendor part number 

in paragraph (j) of AD 2015–02–06, 

Amendment 39–18073 (80 FR 5017, 

January 30, 2015), was incorrectly 

identified as ‘‘845401.’’ The correct 

vendor part number is ‘‘8454–1.’’ 

Since this new AD replaces AD 2015– 

02–06, Amendment 39–18073 (80 FR 

5017, January 30, 2015), there are no 

additional changes in this new AD. 

FAA’s Determination and Requirements 

of This AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are issuing this 

AD because we evaluated all pertinent 

information and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

FAA’s Determination of the Effective 

Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD. The FAA has found that the risk to 

the flying public justifies waiving notice 

and comment prior to adoption of this 

rule because of the urgency to correct 

the part number and AD number errors 

to avoid non-compliance. Therefore, we 

determined that notice and opportunity 

for public comment before issuing this 

AD are impracticable and that good 

cause exists for making this amendment 

effective in fewer than 30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not precede it by notice and 

opportunity for public comment. We 

invite you to send any written relevant 

data, views, or arguments about this AD. 

Send your comments to an address 

listed under the ADDRESSES section. 

Include ‘‘Docket No. FAA–2015–0491; 

Directorate Identifier 2015–NM–019– 

AD’’ at the beginning of your comments. 

We specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this AD because of those 

comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this AD. 

Costs of Compliance 

We estimate that this AD affects 125 

airplanes of U.S. registry. 

The actions required by AD 2015–02– 

06, Amendment 39–18073 (80 FR 5017, 

January 30, 2015), and retained in this 

AD take about 21 work-hours per 

product, at an average labor rate of $85 

per work-hour. Required parts cost 

about $0 per product. Based on these 

figures, the estimated cost of the actions 

that are required by AD 2015–02–06 is 

$1,785 per product. 

The new requirements of this AD add 

no additional economic burden. 

According to the manufacturer, some 

of the costs of this AD may be covered 

under warranty, thereby reducing the 

cost impact on affected individuals. We 

do not control warranty coverage for 

affected individuals. As a result, we 

have included all costs in our cost 

estimate. 

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 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 the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska; and 

4. 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. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 


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Federal Register / Vol. 80, No. 50 / Monday, March 16, 2015 / Rules and Regulations 13485 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA 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 

removing airworthiness directive (AD) 

2015–02–06, Amendment 39–18073 (80 

FR 5017, January 30, 2015), and adding 

the following new AD: 

2015–05–07 Bombardier, Inc.: Amendment 

39–18117. Docket No. FAA–2015–0491; 

Directorate Identifier 2015–NM–019–AD. 

(a) Effective Date 

This AD becomes effective March 16, 2015. 

(b) Affected ADs 

This AD replaces AD 2015–02–06, 

Amendment 39–18073 (80 FR 5017, January 

30, 2015). 

(c) Applicability 

This AD applies to Bombardier, Inc. Model 

CL–600–2B16 (CL–604 Variant) airplanes, 

certificated in any category, serial numbers 

5301 and subsequent, equipped with 

horizontal stabilizer trim actuator (HSTA) 

part number (P/N) 604–92305–3 (vendor P/N 

8454–1) or P/N 604–92305–5 (vendor P/N 

8454–2). 

(d) Subject 

Air Transport Association (ATA) of 

America Code 27, Flight Controls. 

(e) Reason 

This AD was prompted by the discovery of 

three typographical errors in AD 2015–02–06. 

We are issuing this AD to detect and correct 

loose spur gear bolts on the HSTA, which, if 

combined with the failure of the primary 

load path, could lead to failure of the HSTA 

and subsequent loss of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Airplane Flight Manual (AFM) 

Revision, With No Changes 

This paragraph restates the requirements of 

paragraph (g) of AD 2015–02–06, 

Amendment 39–18073 (80 FR 5017, January 

30, 2015), with no changes. Within 30 days 

after March 6, 2015 (the effective date of AD 

2015–02–06: Revise the Normal Procedures 

section of the applicable Bombardier AFM to 

include the information in the applicable 

temporary revision (TR) specified in 

paragraph (g)(1) or (g)(2) of this AD. The TRs 

introduce revised procedures for the 

stabilizer trim system check. Operate the 

airplane according to the limitations and 

procedures in the applicable TR. The 

revision may be done by inserting a copy of 

the applicable TR specified in paragraph 

(g)(1) or (g)(2) of this AD into the AFM. When 

the TR has been included in the general 

revisions of the AFM, the general revisions 

may be inserted into the AFM, provided the 

relevant information in the general revision 

is identical to that in the applicable TR, and 

the TR may be removed. 

(1) Bombardier Temporary Revision (TR) 

604/37, dated May 21, 2013, to the 

Bombardier Challenger CL–604 Airplane 

Flight Manual, PSP 604–1. 

(2) Bombardier TR 605/18, dated May 21, 

2013, to the Bombardier Challenger CL–605 

Airplane Flight Manual, PSP 605–1. 

(h) Retained Maintenance or Inspection 

Program Revision, With No Changes 

This paragraph restates the requirements of 

paragraph (h) of AD 2015–02–06, 

Amendment 39–18073 (80 FR 5017, January 

30, 2015), with no changes. Within 30 days 

after March 6, 2015 (the effective date of AD 

2015–02–06): Revise the maintenance or 

inspection program, as applicable, by 

incorporating procedures for an Operational 

Test (BITE) of the Horizontal Stabilizer Trim 

Controls System (HSTCS), in accordance 

with a method approved by the Manager, 

New York Aircraft Certification Office (ACO), 

ANE–170, FAA; or Transport Canada Civil 

Aviation (TCCA); or Bombardier, Inc.’s TCCA 

Design Approval Organization (DAO). The 

initial compliance time for the operational 

test is within 100 flight hours after March 6, 

2015 (the effective date of AD 2015–02–06). 

Note 1 to paragraph (h) of this AD: 

Bombardier Task 27–41–00–101, Operational 

Test (BITE) of the Horizontal Stabilizer Trim 

Controls System (HSTCS), provides guidance 

for the operational test specified in paragraph 

(h) of this AD. Bombardier Task 27–41–00– 

101 is included in the Bombardier Challenger 

604 Time Limits/Maintenance Checks 

(TLMC) Manual; and in the Bombardier 

Challenger 605 TLMC Manual. 

(i) Retained No Alternative Actions or 

Intervals, With No Changes 

This paragraph restates the requirements of 

paragraph (i) of AD 2015–02–06, Amendment 

39–18073 (80 FR 5017, January 30, 2015), 

with no changes. After the maintenance or 

inspection program has been revised, as 

required by paragraph (h) of this AD, no 

alternative actions (e.g., inspections) or 

intervals may be used unless the actions or 

intervals are approved as an alternative 

method of compliance (AMOC) in 

accordance with the procedures specified in 

paragraph (m)(1) of this AD. 

(j) Retained HSTA Replacement, With 

Corrected Vendor Part Number 

This paragraph restates the requirements of 

paragraph (j) of AD 2015–02–06, Amendment 

39–18073 (80 FR 5017, January 30, 2015), 

with a corrected vendor part number. For 

airplanes equipped with a HSTA having 

P/N 604–92305–3 (vendor P/N 8454–1) or 

P/N 604–92305–5 (vendor P/N 8454–2): 

Within 3,000 flight hours or 26 months after 

March 6, 2015 (the effective date of AD 2015– 

02–06), whichever occurs first, replace any 

HSTA having P/N 604–92305–3 (vendor P/N 

8454–1) or P/N 604–92305–5 (vendor P/N 

8454–2) with a HSTA having P/N 604– 

92305–7 (vendor P/N 8454–3), in accordance 

with the Accomplishment Instructions of 

Bombardier Service Bulletin 604–27–032, 

Revision 02, dated April 22, 2014; or 

Bombardier Service Bulletin 605–27–002, 

Revision 02, dated April 22, 2014; as 

applicable. 

(k) Retained Credit for Previous Actions, 

With No Changes 

This paragraph restates the requirements of 

paragraph (k) of AD 2015–02–06, 

Amendment 39–18073 (80 FR 5017, January 

30, 2015), with no changes. This paragraph 

provides credit for the actions required by 

paragraph (j) of this AD if those actions were 

performed before March 6, 2015 (the effective 

date of AD 2015–02–06) using the service 

information identified in paragraphs (k)(1) 

through (k)(4) of this AD, as applicable. This 

service information is not incorporated by 

reference in this AD. 

(1) Bombardier Service Bulletin 604–27– 

032, dated September 10, 2012. 

(2) Bombardier Service Bulletin 604–27– 

032, Revision 01, dated April 29, 2013. 

(3) Bombardier Service Bulletin 605–27– 

002, dated September 10, 2012. 

(4) Bombardier Service Bulletin 605–27– 

002, Revision 01, April 29, 2013. 

(l) Retained Parts Installation Prohibition, 

With No Changes 

This paragraph restates the requirements of 

paragraph (l) of AD 2015–02–06, Amendment 

39–18073 (80 FR 5017, January 30, 2015), 

with no changes. As of March 6, 2015 (the 

effective date of AD 2015–02–06), no person 

may install any HSTA having P/N 604– 

92305–3 (vendor P/N 8454–1) or 604–92305– 

5 (vendor P/N 8454–2) on any airplane. 

(m) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York ACO, 

ANE–170, FAA, has the authority to approve 

AMOCs for this AD, if requested using the 

procedures found in 14 CFR 39.19. In 

accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the ACO, send it to ATTN: Program 

Manager, Continuing Operational Safety, 

FAA, New York ACO, 1600 Stewart Avenue, 

Suite 410, Westbury, NY 11590; telephone 

516–228–7300; fax 516–794–5531. Before 

using any approved AMOC, notify your 

appropriate principal inspector, or lacking a 

principal inspector, the manager of the local 

flight standards district office/certificate 

holding district office. The AMOC approval 

letter must specifically reference this AD. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, New York ACO, ANE–170; 

or TCCA; or Bombardier, Inc.’s TCCA DAO. 

If approved by the DAO, the approval must 

include the DAO-authorized signature. 


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(n) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2013–18 dated 

July 16, 2013, for related information. This 

MCAI may be found in the AD docket on the 

Internet at http://www.regulations.gov by 

searching for and locating Docket No. FAA– 

2015–0491. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (o)(4) and (o)(5) of this AD. 

(o) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless this AD specifies otherwise. 

(3) The following service information was 

approved for IBR on March 6, 2015 (80 FR 

5017, January 30, 2015). 

(i) Bombardier Service Bulletin 604–27– 

032, Revision 02, dated April 22, 2014. 

(ii) Bombardier Service Bulletin 605–27– 

002, Revision 02, dated April 22, 2014. 

(iii) Bombardier Temporary Revision 604/ 

37, dated May 21, 2013, to the Bombardier 

Challenger CL–604 Airplane Flight Manual, 

PSP 604–1. 

(iv) Bombardier Temporary Revision 605/ 

18, dated May 21, 2013, to the Bombardier 

Challenger CL–605 Airplane Flight Manual, 

PSP 605–1. 

(4) For service information identified in 

this AD, contact Bombardier, Inc., 400 Coˆte 

Vertu Road West, Dorval, Que ́bec H4S 1Y9, 

Canada; telephone 514–855–5000; fax 514– 

855–7401; email thd.crj@

aero.bombardier.com; Internet http://

www.bombardier.com. 

(5) You may view this service information 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

(6) You may view this service information 

that is incorporated by reference 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/cfr/ibrlocations.html. 

Issued in Renton, Washington, on March 5, 

2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–05735 Filed 3–13–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0561; Directorate 

Identifier 2007–NM–223–AD; Amendment 

39–18111; AD 2015–05–01] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all The 

Boeing Company Model 757–200, 

–200PF, –200CB, and –300 series 

airplanes; and Model 767–200, –300, 

–300F, and –400ER series airplanes. 

This AD was prompted by reports 

indicating that the counterweights in 

some hub assemblies of the ram air 

turbine (RAT) could be understrength 

and fracture when the RAT is rotating, 

and that some RAT hub assemblies were 

delivered with balance washer retention 

screws that were incorrectly heattreated, and therefore, susceptible to 

fracture and cracking. This AD requires 

a part number and serial number 

inspection to determine if certain RAT 

hub assemblies are installed; and, for 

affected RAT hub assemblies, doing an 

inspection for missing and fractured 

balance washer screws, and replacement 

or rework if necessary. We are issuing 

this AD to prevent an inoperative RAT, 

which, following a dual engine 

shutdown in flight, will cause loss of all 

hydraulic power to the primary flight 

controls, resulting in subsequent loss of 

control of the airplane. 

DATES: This AD is effective April 20, 

2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of April 20, 2015. 

ADDRESSES: For Boeing service 

information identified in this AD, 

contact Boeing Commercial Airplanes, 

Attention: Data & Services Management, 

P.O. Box 3707, MC 2H–65, Seattle, WA 

98124–2207; telephone 206–544–5000, 

extension 1; fax 206–766–5680; email 

me.boecom@boeing.com; Internet 

https://www.myboeingfleet.com. For 

Hamilton Sundstrand service 

information identified in this AD, 

contact Hamilton Sundstrand, Technical 

Publications, Mail Stop 302–9, 4747 

Harrison Avenue, P.O. Box 7002, 

Rockford, IL 61125–7002; phone: 860– 

654–3575; fax: 860–998–4564; email: 

tech.solutions@hs.utc.com; Internet: 

http://www.hamiltonsundstrand.com. 

You may view this referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, WA. For information on 

the availability of this material at the 

FAA, call 425–227–1221. It is also 

available on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2008– 

0561. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2008– 

0561; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Docket Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Douglas Tsuji, Senior Aerospace 

Engineer, Systems and Equipment 

Branch, ANM–130S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone: 425–917–6546; fax: 425– 

917–6590; Douglas.Tsuji@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a supplemental notice of 

proposed rulemaking (SNPRM) to 

amend 14 CFR part 39 by adding an AD 

that would apply to all The Boeing 

Company Model 757–200, –200PF, 

–200CB, and –300 series airplanes; and 

Model 767–200, –300, –300F, and 

–400ER series airplanes. The SNPRM 

published in the Federal Register on 

April 24, 2014 (79 FR 22777). We 

preceded the SNPRM with a notice of 

proposed rulemaking (NPRM) that 

published in the Federal Register on 

May 20, 2008 (73 FR 29087). The NPRM 

proposed to require doing an inspection 

to determine the part number and serial 

number of the RAT hub assembly, and 

replacing the RAT hub assembly with a 

new, serviceable, or reworked and reidentified RAT hub assembly if 

necessary. The NPRM was prompted by 

reports indicating that the 

counterweights in some hub assemblies 

of the RATs could be understrength and 

fracture when the RAT is rotating. The 


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