680 Federal Register / Vol. 70, No. 3 / Wednesday, January 5, 2005 / Rules and Regulations 

ADDRESSES section for a location to 

examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety.

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 adding 

the following new airworthiness 

directive (AD):

2005–01–03 Boeing: Amendment 39–13927. 

Docket No. FAA–2004–19200; 

Directorate Identifier 2003–NM–195–AD. 

Effective Date 

(a) This AD becomes effective February 9, 

2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Boeing Model 747–

100, –100B, –100B SUD, –200B, –200C, 

–200F, and –300 series airplanes; and Model 

747SP and 747SR series airplanes; 

certificated in any category; equipped with 

Pratt & Whitney JT9D–3, and –7 (except –70) 

series engines or General Electric CF6–50 

series engines with modified JT9D–7 inboard 

struts; as listed in Boeing Alert Service 

Bulletin 747–54A2219, dated September 4, 

2003. 

Unsafe Condition 

(d) This AD was prompted by reports of 

cracking in the midspar web. We are issuing 

this AD to detect and correct cracking in the 

midspar assembly, which could result in the 

loss of the midspar assembly load path, and 

could, combined with the loss of the nacelle 

station 180 bulkhead load path, lead to the 

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. 

Compliance Times 

(f) Within 18 months after the effective 

date of this AD, do the actions in paragraphs 

(g) and (h) of this AD, as applicable. Repeat 

the actions thereafter at intervals not to 

exceed 1,200 flight cycles. 

Inboard Strut Midspar Inspection 

(g) For Group 1 and 2 airplanes specified 

in paragraph 1.A.1. of Boeing Alert Service 

Bulletin 747–54A2219, dated September 4, 

2003: Perform a detailed inspection of the 

midspar web of the inboard struts for 

cracking, disbonding, or buckling; a detailed 

inspection of the midspar stiffeners for any 

crack or fracture; related investigative 

actions; and any applicable corrective 

actions; in accordance with ‘‘Part 1’’ of the 

Work Instructions of Boeing Alert Service 

Bulletin 747–54A2219, dated September 4, 

2003; except as required by paragraph (i) of 

this AD. Perform any related investigative 

actions and any applicable corrective actions 

before further flight. 

Outboard Strut Midspar Inspection 

(h) For Group 1 airplanes specified in 

paragraph 1.A.1. of Boeing Alert Service 

Bulletin 747–54A2219, dated September 4, 

2003: Perform a detailed inspection of the 

midspar web of the outboard struts for 

cracking, disbonding, or buckling; a detailed 

inspection of the midspar stiffeners for any 

crack or fracture; related investigative 

actions; and any applicable corrective 

actions; in accordance with ‘‘Part 2’’ of the 

Work Instructions of Boeing Alert Service 

Bulletin 747–54A2219, dated September 4, 

2003; except as required by paragraph (i) of 

this AD. Perform any related investigative 

actions and any applicable corrective actions 

before further flight. 

Contact the FAA/Designated Engineering 

Representative (DER) 

(i) Where Boeing Alert Service Bulletin 

747–54A2219, dated September 4, 2003, 

specifies to contact Boeing for appropriate 

action: Before further flight, repair per a 

method approved by the Manager, Seattle 

Aircraft Certification Office (ACO), FAA; or 

per data meeting the type certification basis 

of the airplane approved by a Boeing 

Company DER who has been authorized by 

the Manager, Seattle ACO, to make such 

findings. For a repair method to be approved, 

the approval must specifically reference this 

AD. 

Alternative Methods of Compliance 

(AMOCs) 

(j)(1) The Manager, Seattle ACO, FAA, has 

the authority to approve AMOCs for this AD, 

if requested in accordance with the 

procedures found in 14 CFR 39.19. 

(2) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD, if it is approved by a 

Boeing Company DER who has been 

authorized by the Manager, Seattle ACO, to 

make those findings. For a repair method to 

be approved, the approval must specifically 

refer to this AD. 

Material Incorporated by Reference 

(k) You must use Boeing Alert Service 

Bulletin 747–54A2219, dated September 4, 

2003, to perform the actions that are required 

by this AD, unless the AD specifies 

otherwise. The Director of the Federal 

Register approves the incorporation by 

reference of this document in accordance 

with 5 U.S.C. 552(a) and 1 CFR part 51. For 

copies of the service information, contact 

Boeing Commercial Airplanes, P.O. Box 

3707, Seattle, Washington 98124–2207. For 

information on the availability of this 

material at the National Archives and 

Records Administration (NARA), call (202) 

741–6030, or go to http://www.archives.gov/

federal_register/code_of_federal_regulations/

ibr_locations.html.

You may view the AD docket at the Docket 

Management Facility, U.S. Department of 

Transportation, 400 Seventh Street SW., 

room PL–401, Nassif Building, Washington, 

DC.

Issued in Renton, Washington, on 

December 27, 2004. 

Kevin M. Mullin, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 05–105 Filed 1–4–05; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39

[Docket No. 2004–NE–19–AD; Amendment 

39–13917; AD 2004–26–05] 

RIN 2120–AA64

Airworthiness Directives; Rolls-Royce 

plc RB211–524 Series Turbofan 

Engines

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Final rule.

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD) for 

certain Rolls-Royce plc (RR) RB211–524 

series turbofan engines. That AD 

currently requires initial and repetitive 

borescope insepctions of the head 

section and meterpanel assembly of the 

combustion liner, and replacement, if 

necessary, with serviceable parts. In 

addition, that AD allows an optional 

installation of a front combustion liner 

with a strengthened head section as a 

terminating action to the inspection 

requirements. This AD requires initial 

and repetitive borescope inspections of 

the head section and meterpanel 

assembly of the combustion liner, and 

replacement if necessary with 

serviceable parts. This AD also requires 

reduction of the inspection intervals of 

certain RB211–524 engine models that 

have not been repaired to RR Field 

Repair Scheme FRS5367/B, and a 

mandatory terminating action to be 

completed by a certain date. This AD 

results from five events that are directly 

attributed to combustor head breakup 

and meterpanel failure which were 

found at overhaul inspection. At least 

one of these events resulted in a 

combustion case burn-through. We are 

issuing this AD to prevent engine 

combustion liner deterioration, which

Federal Register / Vol. 70, No. 3 / Wednesday, January 5, 2005 / Rules and Regulations 681

can result in combustion liner breakup, 

case burn-through, and engine fire.

DATES: This AD becomes effective 

February 9, 2005. The incorporation by 

reference of RR ASB RB.211–72–AB482, 

Revision 9, dated July 28, 2003; RollsRoyce Service Bulletins (SB’s) RB.211–

72–9764, Revision 3, dated January 16, 

1998, RB.211–72–9670, Original Issue, 

dated August 27, 1993; and RB.211–72–

9764 Supplement 1, dated January 16, 

1998; are approved by the Director of 

the Federal Register as of February 9, 

2005.

ADDRESSES: You can get the service 

information identified in this AD from 

Rolls-Royce plc, P.O. Box 31, Derby, 

DE24–8BJ, United Kingdom; telephone: 

011–44–1332–242424; fax 011–44–

1332–249936. 

You may examine the AD docket at 

the FAA, New England Region, Office of 

the Regional Counsel, 12 New England 

Executive Park, Burlington, MA. You 

may examine the service information, at 

the FAA, New England Region, Office of 

the Regional Counsel, 12 New England 

Executive Park, Burlington, MA; or at 

the National Archives and Records 

Administration (NARA). For 

information on the availability of this 

material at NARA, call 202–741–6030, 

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

federal_register/

code_of_federal_regulations/

ibr_locations.html.

FOR FURTHER INFORMATION CONTACT: Ian 

Dargin, Aerospace Engineer, Engine 

Certification Office, FAA, Engine and 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803–

5299; telephone (781) 238–7178; fax 

(781) 238–7199.

SUPPLEMENTARY INFORMATION: The FAA 

proposed to amend 14 CFR part 39 with 

a proposed AD. The proposed AD 

applies to RR RB211–524 series turbofan 

engines. We published the proposed AD 

in the Federal Register on May 18, 2004 

(69 FR 28094). That action proposed to 

require initial and repetitive borescope 

inspections of the head section and 

meterpanel assembly of the combustion 

liner and replacement if necessary, with 

serviceable parts. That action also 

proposed a reduction of the inspection 

intervals of certain RB211–524 engine 

models that have not been repaired to 

RR Field Repair Scheme FRS53667/B, 

and a mandatory terminating action to 

be completed by a certain date. 

Examining the AD Docket 

You may examine the AD Docket 

(including any comments and service 

information), by appointment, between 

8 a.m. and 4:30 p.m., Monday through 

Friday, except Federal holidays. See

ADDRESSES for the location. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We received no 

comments on the proposal or on the 

determination of the cost to the public. 

However, we corrected RR Service 

Bulletin (SB) No. RB.211–71–9670 in 

Compliance paragraph (q) of this AD to 

RR SB No. RB.211.–72–9670. 

Conclusion 

We have carefully reviewed the 

available data and determined that air 

safety and the public interest require 

adopting the AD with the change 

described previously. We have 

determined that the change will neither 

increase the economic burden on any 

operator nor increase the scope of the 

AD. 

Costs of Compliance 

There are about 537 RB211–524 series 

turbofan engines of the affected design 

in the worldwide fleet. We estimate that 

18 engines installed on airplanes of U.S. 

registry will be affected by this AD. We 

also estimate that it will take 

approximately 2.0 work hours per 

engine to perform the actions, and that 

the average labor rate is $65 per work 

hour. Required parts will cost about 

$228,389 per engine. Based on these 

figures, we estimate that total cost of the 

AD to U.S. operators to be $4,113,342. 

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 by sending a request to us 

at the address listed under ADDRESSES. 

Include ‘‘AD Docket No. 2004–NE–19–

AD’’ in your request.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

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 

removing Amendment 39–9978 (62 FR 

16475, April 7, 1997) and by adding a 

new airworthiness directive, 

Amendment 39–13917, to read as 

follows:

2004–26–05 Rolls-Royce plc: Amendment 

39–13917. Docket No. 2004–NE–19–AD. 

Supersedes AD 97–07–04, Amendment 

39–9978. 

Effective Date 

(a) This AD becomes effective February 9, 

2005. 

Affected ADs 

(b) This AD supersedes AD 97–07–04, 

Amendment 39–9978. 

Applicability 

(c) This AD applies to Rolls-Royce plc (RR) 

engine models RB211–524B–02, –524B2, 

–524B3, –524B4, –524C2, and –524D4 series 

engines incorporating RR Service Bulletin 

(SB) No. RB.211–72–7221 or RR SB No. 

RB.211–72–7998 with front combustion liner

682 Federal Register / Vol. 70, No. 3 / Wednesday, January 5, 2005 / Rules and Regulations 

assembly, part number (P/N) UL16885, 

UL29916, UL27107, UL28972, or UL28974 

installed but not incorporating RR SB No. 

RB.211–72–9670 or RR SB No. RB.211–72–

9764, and engine models RB211–524G and 

–524H series engines with front combustion 

liner assembly P/N UL27659, UL23992, or 

UL22988 but not incorporating RR SB No. 

RB.211–72–9764. These engines are installed 

on, but not limited to, Boeing 747 and 

Lockheed L1011 series airplanes. 

Unsafe Condition 

(d) This AD results from five events that 

are directly attributed to combustor head 

breakup and meterpanel failure which were 

found at overhaul inspection. At least one of 

these events resulted in a combustion case 

burn-through. The actions specified in this 

AD are intended to prevent engine 

combustion liner deterioration, which can 

result in combustion liner breakup, case 

burn-through, and engine fire. 

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. Engine 

inspections previously made to RR Service 

Bulletin No. RB.211–72–B482, Revision 8, 

can be credited for counting cycles since last 

inspection. 

Inspections of Combustion Liner Head 

Sections—Not Previously Repaired 

(f) Borescope-inspect combustion liner 

head sections that have not been previously 

repaired. Use paragraphs 3.A.(1) through 

3.A.(5) of the Accomplishment Instructions 

of RR Alert Service Bulletin (ASB) No. 

RB.211–72–AB482, Revision 9, dated July 28, 

2003, and the compliance thresholds in Table 

1 of this AD.

TABLE 1.—COMBUSTOR HEAD SECTION—NOT PREVIOUSLY REPAIRED

Engine series Initial inspection (cycles since-new 

(CSN)) 

Repetitive inspection (cyclessince-last-inspection (CSLI)) Parts exceeding initial inspection 

cycles (cycles-in-service (CIS)) 

(1) RB211–524C2, –524D4, 

–524G, and –524H.

Within 1,400 to 1,600 CSN .......... Within 200 CSLI ........................... Within 100 CIS after the effective 

date of this AD. 

(2) RB211–524B–02, –524B, 

–524B3, and –524B4.

Within 3,000 to 3,200 CSN .......... Within 200 CSLI ........................... Within 200 CIS after the effective 

date of this AD. 

Inspections of Combustion Head Sections—

Previously Repaired Using RR Field Repair 

Scheme FRS5367/B 

(g) Borescope-inspect combustion liner 

head sections previously repaired using RR 

Field Repair Scheme FRS5367/B. Use 

paragraphs 3.A.(1) through 3.A.(5) of the 

Accomplishment Instructions of RR ASB No. 

RB.211–72–AB482, Revision 9, dated July 28, 

2003, and the compliance thresholds in Table 

2 of this AD.

TABLE 2.—COMBUSTOR HEAD SECTION—PREVIOUSLY REPAIRED USING RR FIELD REPAIR SCHEME FRS5367/B 

Engine series Initial inspection (cycles-sincelast-repair (CSLR)) 

Repetitive inspection (cyclessince-last-inspection (CSLI)) Parts exceeding initial inspection 

cycles (cycles-in-service (CIS)) 

(1) RB211–524C2, –524D4, 

–524G, and –524H.

Within 1,800 to 2,200 CSLR ........ Within 400 CSLI ........................... Within 200 CIS after the effective 

date of this AD. 

(2) RB211–524B–02, –524B2, 

–524B3, and –524B4.

Within 3,000 to 3,200 CSLR ........ Within 400 CSLI ........................... Within 200 CIS after the effective 

date of this AD. 

Inspections of Combustion Head Sections 

That Have Been Repaired But Did Not Use 

RR Field Repair Scheme FRS5367/B 

(h) Borescope-inspect combustion liner 

sections that have been repaired using a 

method other than RR Field Repair Scheme 

FRS5367/B. Use paragraphs 3.A.(1) through 

3.A.(5) of the Accomplishment Instructions 

of RR ASB No. RB.211–72–AB482, Revision 

9, dated July 28, 2003, and the compliance 

thresholds in Table 3 of this AD.

TABLE 3.—COMBUSTOR HEAD SECTION—REPAIRED, BUT DID NOT USE RR FIELD REPAIR SCHEME FRS5367/B 

Engine series Initial inspection cycles (cyclessince-last-repair (CSLR)) 

Repetitive inspection cycles (cycles-since-last-inspection (CSLI)) Parts exceeding initial inspection 

cycles (cycles-in-service (CIS)) 

(1) RB211–524C2, –524D4, 

–524G, and –524H.

Within 500 to 700 CSLR .............. Within 200 CSLI ........................... Within 100 CIS after the effective 

date of this AD. 

(2) RB211–524B–02, –524B2, 

–524B3, and –524B4.

Within 2,000 to 2,200 CSLR ........ Within 200 CSLI ........................... Within 200 CIS after the effective 

date of this AD. 

Note 1: For an installed front combustion 

liner that is subject to RR ASB No. RB.211–

72–AB482, Revision 9, dated July 28, 2003: 

If the operator can confirm with the relevant 

overhaul base or repair vendor that the 

nicrobraze repair RR Field Repair Scheme 

FRS5367 has been applied to all 18 struts, 

then this is equivalent to compliance with RR 

Field Repair Scheme FRS5367/B.

Note 2: Head sections repaired by 

replacement of all 18 struts using RR Field 

Repair Scheme FRS6548 are considered as 

equivalent to fitting a new head section for 

inspection purposes.

Inspections of Meterpanel Assemblies—Not 

Repaired 

(i) Borescope-inspect meterpanel 

assemblies, incorporating Service Bulletin 

(SB) No. RB.211–72–7998, that have not been 

previously repaired. Using Paragraphs 3.B.(1) 

through 3.B.(7) of the Accomplishment 

Instructions of RR ASB No. RB.211–72–

AB482, Revisions 9, dated July 28, 2003, and 

the compliance thresholds in Table 4 of this 

AD.

Federal Register / Vol. 70, No. 3 / Wednesday, January 5, 2005 / Rules and Regulations 683

TABLE 4.—METERPANEL ASSEMBLY—NOT REPAIRED

Engine series Initial inspection cycles-since-new 

(CSN) 

Repetitive inspection cycles (cycles-since-last-inspection (CSLI)) Parts exceeding initial inspection 

cycles (cycles-in-service (CIS)) 

(1) RB211–524D4, –524G, and 

–524H.

Within 1,000 to 1,200 CSN .......... Within 400 CSLI ........................... Within 50 CIS after the effective 

date of this AD. 

(2) RB211–524D4, –524G, and 

–524H that have not used 

RB211–524H ratings at any time.

Within 1,800 to 2,000 CSN .......... Within 400 CSLI ........................... Within 50 CIS after the effective 

date of this AD. 

Inspections of Meterpanel Assemblies—

Repaired 

(J) Borescope-inspect meterpanel 

assemblies, incorporating Service Bulletin 

(SB) No. RB.211–72–7998, that have been 

previously repaired. Use paragraphs 3.B.(1) 

through 3.B.(7) of the Accomplishment 

Instructions of RR ASB No. RB.211–72–

AB482, Revision 9, dated July 28, 2003, and 

the compliance thresholds in Table 5 of this 

AD.

TABLE 5.—METERPANEL ASSEMBLY—REPAIRED

Engine series Initial inspection cycles (cyclessince-last-repair (CSLR)) 

Repetitive inspection cycles (cycles-since-last-inspection (CSLI)) Parts exceeding initial inspection 

cycles (cycles-in-service (CIS)) 

(1) RB211–524D4, –524G, and 

–524H.

Within 500 to 700 CSLR .............. Within 400 CSLI ........................... Within 50 CIS after the effective 

date of this AD. 

Note 3: There is no requirement to inspect 

meter panels for combustors to a pre-RR SB 

No. RB.211–72–7998 standard.

Reject Parts 

(k) Replace parts that exceed the 

acceptance criteria. Information about the 

acceptance criteria can be found in the 

Aircraft Maintenance Manual, 72–00–00, 

Inspection/Check. 

Mandatory Terminating Action 

(l) Replace any front combustion liner 

assembly that has a P/N listed in paragraph 

(c) of this AD at the next shop visit or within 

10,000 CSN but no later than December 31, 

2012.

(m) Replacement of the front combustion 

liner assembly with a front combustion liner 

assembly that incorporates the modifications 

in RR SB No. RB.211–72–9670 or RR SB No. 

RB.211–72–9764 in the RB211–524B02, 

–524B2, –524B3, –524B4, –524C2 and 

–524D4 engines constitutes terminating 

action to the repetitive inspections in 

paragraphs (f), (g), (h), (i), and (j), of this AD. 

(n) Replacement of the front combustion 

liner assembly with a front combustion liner 

assembly that incorporates the modifications 

in RR SB No. RB.211–72–9764 in the RB211–

524G and –524H engines constitutes 

terminating action to the repetitive 

inspections in paragraphs (f), (g), (h), (i), and 

(j) of this AD. 

Definition of Shop Visit 

(o) For the purpose of this AD, a shop visit 

is defined as any time that the 04 module is 

removed for refurbishment or overhaul. 

Alternative Methods of Compliance 

(p) 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. 

Material Incorporated by Reference 

(q) You must use the Rolls-Royce plc (RR) 

Alert Service Bulletin (ASB) and Service 

Bulletins (SB’s) listed in Table 6 of this AD 

to do the inspections and replacements 

required by this AD. The Director of the 

Federal Register approved the incorporation 

by reference of RR ASB No. RB.211–72–

AB482, Revision 9, dated July 28, 2003; SB’s 

No. RB.211–72–9764, Revision 3, dated 

January 16, 1998, No. RB.211–72–9670, 

Original Issue, dated August 27, 1993; and 

SB No. RB.211–72–9764 Supplement, 

Revision 1, dated January 16, 1998; in 

accordance with 5 U.S.C. 552(a) and 1 CFR 

part 51. You can get copies at the FAA, New 

England Region, Office of the Regional 

Counsel, 12 New England Executive Park, 

Burlington, MA; 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. Table 6 follows:

TABLE 6.—INCORPORATION BY REFERENCE

Service bulletin Page number(s) shown on the 

page Revision level shown on the page Date shown on the page 

RB.211–72–AB482, ................................................... All .................................................. 9 .................................................... July 28, 2003. 

Total Pages: 12 

RB.211–72–9670, ...................................................... All .................................................. Original .......................................... Aug. 27, 1993. 

Total Pages: 49 

RB.211–72–9764 ....................................................... 1 ....................................................

2 ....................................................

3, 4 ................................................

5 ....................................................

3 ....................................................

Original ..........................................

3 ....................................................

1 ....................................................

Jan. 16, 1998. 

Aug. 20, 1993. 

Jan. 16, 1998. 

Aug. 25, 1995. 

6 ....................................................

7–10 ..............................................

11 ..................................................

12–30 ............................................

3 ....................................................

Original ..........................................

3 ....................................................

Original ..........................................

Jan. 16, 1998. 

Aug. 20, 1993. 

Jan. 16, 1998. 

Aug. 20, 1993. 

Total Pages: 30 

RB.211–72–9764 Supplement .................................. 1 .................................................... 1 .................................................... Jan. 16, 1998. 

Total Pages: 1 

684 Federal Register / Vol. 70, No. 3 / Wednesday, January 5, 2005 / Rules and Regulations 

Related Information 

(r) Civil Aviation Authority airworthiness 

directive AD G–2003–0011, dated October 1, 

2003, (previously 005–07–95, dated 

November 15, 2001), also addresses the 

subject of this AD. Aircraft Maintenance 

Manual 72–00–00 also addresses the subject 

of this AD.

Issued in Burlington, Massachusetts, on 

December 20, 2004. 

Francis A. Favara, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service.

[FR Doc. 05–85 Filed 1–4–05; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39

[Docket No. FAA–2004–19496; Directorate 

Identifier 2003–NM–181–AD; Amendment 

39–13920; AD 2004–26–08] 

RIN 2120–AA64

Airworthiness Directives; Bombardier 

Model CL–215–6B11 (CL215T Variant) 

and CL–215–6B11 (CL415 Variant) 

Series Airplanes

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Final rule.

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Bombardier Model CL–215–6B11 

(CL215T variant) and CL–215–6B11 

(CL415 variant) series airplanes. This 

AD requires replacing the mounting pad 

studs of the auxiliary feather pump with 

new, longer studs, and installing a 

pressure relief valve. This AD is 

prompted by a few incidents of external 

oil leaks from the oil pump of the power 

control unit due to a malfunction of the 

pressure regulating valve. We are 

issuing this AD to prevent fracturing of 

the pump body, which could result in 

loss of engine oil, and consequent 

inability to maintain engine oil pressure 

and to feather the propeller.

DATES: This AD becomes effective 

February 9, 2005. 

The incorporation by reference of 

certain publications listed in the AD is 

approved by the Director of the Federal 

Register as of February 9, 2005.

ADDRESSES: For service information 

identified in this AD, contact 

Bombardier, Inc., Canadair, Aerospace 

Group, P.O. Box 6087, Station Centreville, Montreal, Quebec H3C 3G9, 

Canada. You can examine this 

information 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. 

You can examine the contents of this 

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–2004–

19496; the directorate identifier for this 

docket is 2003–NM–181–AD.

FOR FURTHER INFORMATION CONTACT:

Richard Fiesel, 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) 228–7304; fax 

(516) 794–5531. 

Examining the Docket 

The AD docket contains the proposed 

AD, comments, and any final 

disposition. You can 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.

SUPPLEMENTARY INFORMATION: The FAA 

proposed to amend 14 CFR part 39 with 

an AD for certain Bombardier Model 

CL–215–6B11 (CL215T variant) and CL–

215–6B11 (CL415 variant) series 

airplanes. That action, published in the 

Federal Register on November 3, 2004 

(69 FR 63968), proposed to require 

replacing the mounting pad studs of the 

auxiliary feather pump with new, longer 

studs, and installing a pressure relief 

valve. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. No comments 

have been submitted on the proposed 

AD or on the determination of the cost 

to the public. 

Conclusion 

We have carefully reviewed the 

available data and determined that air 

safety and the public interest require 

adopting the AD as proposed. 

Costs of Compliance 

The following table provides the 

estimated costs for U.S. operators to 

comply with this AD.

ESTIMATED COSTS

Action Work

hours 

Average

labor rate

per hour 

Parts Cost per

airplane 

Number

of U.S.-

registered

airplanes 

Fleet cost 

Replacement ..................................... 2 $65 Free .................................................. $130 3 $390 

Installation ......................................... 4 65 Free .................................................. 260 3 780 

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