Federal Register / Vol. 70, No. 119 / Wednesday, June 22, 2005 / Rules and Regulations 35989

2005–13–02 Bombardier, Inc. (Formerly 

Canadair): Amendment 39–14138. 

Docket No. FAA–2004–19754; 

Directorate Identifier 2004–NM–181–AD. 

Effective Date 

(a) This AD becomes effective July 27, 

2005. 

Affected ADs 

(b) None. 

Applicability: (c) This AD applies to the 

airplanes listed in Table 1 of this AD, 

certificated in any category, excluding those 

airplanes on which Modification Summaries 

670T00494 or 670T11944; and Modification 

Summary 670T11508 or Bombardier Service 

Bulletin 670BA–29–008, dated March 12, 

2004, or Revision A, dated May 5, 2004; has 

been incorporated in production.

TABLE 1.—APPLICABILITY

Bombardier model Serial numbers 

(1) CL–600–2C10 (Regional Jet Series 700 & 701) series airplanes .................................................................. 10003 through 10999 inclusive. 

(2) CL–600–2D24 (Regional Jet Series 900) series airplanes ............................................................................. 15001 through 15990 inclusive. 

Unsafe Condition 

(d) This AD was prompted by reports of 

hydraulic pressure loss in either the number 

1 or number 2 hydraulic system due to 

breakage or leakage of hydraulic lines in the 

aft equipment bay and reports of cracks on 

the aft pressure bulkhead web around these 

feed-through holes. We are issuing this AD to 

prevent loss of hydraulic pressure, which 

could result in reduced controllability of the 

airplane, and to detect and correct cracks on 

the aft pressure bulkhead web, which could 

result in reduced structural integrity of the 

aft pressure bulkhead. 

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. 

Revision of Airworthiness Limitations 

Section 

(f) Within 30 days after the effective date 

of this AD, revise the Airworthiness 

Limitations section of the Instructions of 

Continued Airworthiness by inserting a copy 

of the new repetitive inspections and an 

optional terminating action of Bombardier 

CRJ 700/900 Series Temporary Revision (TR) 

MRM2–129, dated June 1, 2004, into Section 

1.4, Part 2 (Airworthiness Limitations), of 

Bombardier Regional Jet Model CL–600–2C10 

and CL–600–2D24 Maintenance 

Requirements Manual, CSP B–053. 

Thereafter, except as provided in paragraph 

(h)(2) or (i) of this AD, no alternative 

structural inspection intervals may be 

approved for this aft pressure bulkhead and 

pylon pressure pan in the vicinity of the 

hydraulic fittings and the hydraulic tube 

adapters. 

(g) When the information in TR MRM2–

129, dated June 1, 2004, is included in the 

general revisions of the Maintenance 

Requirement Manual, the general revisions 

may be inserted into the Airworthiness 

Limitations section of the Instructions of 

Continued Airworthiness and this TR may be 

removed. 

Corrective Action 

(h) If any crack is found during any 

inspection done in accordance with 

Bombardier CRJ 700/900 Series TR MRM2–

129, dated June 1, 2004, or the same 

inspection specified in the general revisions 

of the Maintenance Requirement Manual, do 

the actions specified in paragraphs (h)(1) and 

(h)(2) of this AD.

(1) Before further flight, repair the crack in 

accordance with a method approved by 

either the Manager, New York Aircraft 

Certification Office (ACO), FAA; or Transport 

Canada Civil Aviation (TCCA) (or its 

delegated agent). 

(2) At the applicable time specified in 

paragraph (h)(2)(i) or (h)(2)(ii) of this AD, 

revise the Airworthiness Limitations section 

of the Instructions of Continued 

Airworthiness by inserting a copy of the 

inspection requirements for the repair 

required by paragraph (h)(1) of this AD into 

Section 1.4, Part 2 (Airworthiness 

Limitations), of Bombardier Regional Jet 

Model CL–600–2C10 and CL–600–2D24 

Maintenance Requirements Manual, CSP B–

053. Thereafter, except as provided in 

paragraph (i) of this AD, no alternative 

structural inspection intervals may be 

approved for this aft pressure bulkhead and 

pylon pressure pan in the vicinity of the 

hydraulic fittings, and the hydraulic tube 

adapters. 

(i) If the repair required by paragraph (h)(1) 

of this AD is done after the effective date of 

this AD: Revise the Airworthiness 

Limitations section within 12 months after 

the repair. 

(ii) If the repair required by paragraph 

(h)(1) of this AD was accomplished before the 

effective date of this AD: Revise the 

Airworthiness Limitations section within 12 

months after the repair or 30 days after the 

effective date of this AD, whichever occurs 

later. 

Alternative Methods of Compliance 

(AMOCs) 

(i) The Manager, New York ACO, FAA, has 

the authority to approve AMOCs for this AD, 

if requested in accordance with the 

procedures found in 14 CFR 39.19. 

Related Information 

(j) Canadian airworthiness directive CF–

2004–14, dated July 20, 2004, also addresses 

the subject of this AD. 

Material Incorporated by Reference 

(k) You must use Bombardier CRJ 700/900 

Series Temporary Revision MRM2–129, 

dated June 1, 2004, 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. To 

get copies of the service information, contact 

Bombardier, Inc., Canadair, Aerospace 

Group, P.O. Box 6087, Station Centre-ville, 

Montreal, Quebec H3C 3G9, Canada. To view 

the AD docket, contact the Docket 

Management Facility, U.S. Department of 

Transportation, 400 Seventh Street SW., 

room PL–401, Nassif Building, Washington, 

DC. To review copies of the service 

information, go to the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at the NARA, call (202) 741–6030, 

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

federal_register/code_of_federal 

_regulations/ibr_locations.html.

Issued in Renton, Washington, on June 10, 

2005. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 05–12000 Filed 6–21–05; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39

[Docket No. FAA–2004–19678; Directorate 

Identifier 2004–NM–62–AD; Amendment 39–

14141; AD 2005–13–05] 

RIN 2120–AA64

Airworthiness Directives; Boeing 

Model 747–400F Series Airplanes

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT).

ACTION: Final rule.

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Boeing Model 747–400F series 

airplanes. This AD requires initial 

detailed and open-hole high frequency 

eddy current inspections for cracking of 

the web, upper chord, and upper chord 

strap of the upper deck floor beams, and 

repair of any cracking. This AD also 

requires a preventive modification of 

the upper deck floor beams, and 

repetitive inspections for cracking after 

35990 Federal Register / Vol. 70, No. 119 / Wednesday, June 22, 2005 / Rules and Regulations 

accomplishing the modification. This 

AD is prompted by reports of fatigue 

cracking found on the upper deck floor 

beam to frame attachment points. We 

are issuing this AD to prevent fatigue 

cracks in the upper chord, upper chord 

strap, and the web of the upper deck 

floor beams and resultant failure of the 

floor beams. Failure of a floor beam 

could result in damage to critical flight 

control cables and wire bundles that 

pass through the floor beam, and 

consequent loss of controllability of the 

airplane. Failure of the floor beam also 

could result in the failure of the 

adjacent fuselage frames and skin, and 

consequent rapid decompression of the 

airplane.

DATES: This AD becomes effective July 

27, 2005. 

The incorporation by reference of a 

certain publication listed in the AD is 

approved by the Director of the Federal 

Register as of July 27, 2005.

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, P.O. Box 3707, 

Seattle, Washington 98124–2207. 

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 U.S. Department of Transportation, 

400 Seventh Street SW., room PL–401, 

Washington, DC. This docket number is 

FAA–2004–19678; the directorate 

identifier for this docket is 2004–NM–

62–AD.

FOR FURTHER INFORMATION CONTACT: Ivan 

Li, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 917–6437; 

fax (425) 917–6590.

SUPPLEMENTARY INFORMATION: The FAA 

proposed to amend 14 CFR part 39 with 

an AD for certain Boeing Model 747–

400F series airplanes. That action, 

published in the Federal Register on 

November 24, 2004 (69 FR 68277), 

proposed to require initial detailed and 

open-hole high frequency eddy current 

inspections for cracking of the web, 

upper chord, and upper chord strap of 

the upper deck floor beams, and repair 

of any cracking. That action also 

proposed to require a preventive 

modification of the upper deck floor 

beams, and repetitive inspections for 

cracking after accomplishing the 

modification.

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 

This AD affects about 53 airplanes 

worldwide and 13 airplanes of U.S. 

registry. The following table provides 

the estimated costs for U.S. operators to 

comply with this AD, depending on the 

airplane configuration:

ESTIMATED COSTS

Action Work hours 

Average 

labor rate 

per hour 

Parts Cost per

airplane 

Number of affected U.S.-

registered

airplanes 

Fleet cost 

Pre-modification inspections ...................................... 11 ................ $65 $0 ................ $715 ............ 13 $9,295

Modification/Inspections done during modification .... 498 or 524 ... 65 $13,554 or 

$14,874.

$45,924 or 

$48,934.

13 $597,012 or 

$636,142

Post-modification inspections .................................... 66 ................ 65 $0 ................ $4,290, per 

inspection 

cycle.

13 $55,770

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 regulatory evaluation 

of the estimated costs to comply with 

this AD. 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, 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:

Federal Register / Vol. 70, No. 119 / Wednesday, June 22, 2005 / Rules and Regulations 35991

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):

2005–13–05 Boeing: Amendment 39–14141. 

Docket No. FAA–2004–19678; 

Directorate Identifier 2004–NM–62–AD. 

Effective Date 

(a) This AD becomes effective July 27, 

2005. 

Affected ADs 

(b) None. 

Applicability: (c) This AD applies to Model 

747–400F series airplanes, certificated in any 

category, as listed in Boeing Alert Service 

Bulletin 747–53A2443, dated May 9, 2002. 

Unsafe Condition 

(d) This AD was prompted by reports of 

fatigue cracking found on the upper deck 

floor beam to frame attachment points. We 

are issuing this AD to prevent fatigue cracks 

in the upper chord, upper chord strap, and 

web of the upper deck floor beams and the 

resultant failure of the floor beams. Failure of 

a floor beam could result in damage to 

critical flight control cables and wire bundles 

that pass through the floor beam, and 

consequent loss of controllability of the 

airplane. Failure of the floor beam also could 

result in the failure of the adjacent fuselage 

frames and skin, and consequent rapid 

decompression of 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. 

Service Bulletin Reference 

(f) For the purposes of this AD, the term 

‘‘service bulletin’’ means the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2443, dated May 9, 

2002. 

Inspections/Repair/Modification 

(g) Before the accumulation of 15,000 total 

flight cycles, or within 1,000 flight cycles 

after the effective date of this AD, whichever 

is later: Accomplish detailed and open-hole 

high frequency eddy current (HFEC) 

inspections for cracking of the web, upper 

chord, and upper chord strap of the upper 

deck floor beams, by doing all the applicable 

actions in accordance with Part 3.B.1. of the 

service bulletin.

Note 1: For the purposes of this AD, a 

detailed inspection is: ‘‘An intensive 

examination of a specific item, installation, 

or assembly to detect damage, failure, or 

irregularity. Available lighting is normally 

supplemented with a direct source of good 

lighting at an intensity deemed appropriate. 

Inspection aids such as mirror, magnifying 

lenses, etc., may be necessary. Surface 

cleaning and elaborate procedures may be 

required.’’

(h) If any crack is found during any 

inspection required by paragraph (g) of this 

AD: Before further flight, accomplish the 

actions required by paragraph (h)(1) and 

(h)(2) of this AD. 

(1) Repair in accordance with the service 

bulletin; except where the service bulletin 

specifies to contact Boeing for appropriate 

action, before further flight, repair in 

accordance with a method approved by the 

Manager, Seattle Aircraft Certification Office 

(ACO), FAA; or according to data meeting the 

type certification basis of the airplane 

approved by a Boeing Company Designated 

Engineering Representative (DER) who has 

been authorized by the Manager, Seattle 

ACO, to make such findings. For a repair 

method to be approved by the Manager, 

Seattle ACO, as required by this paragraph, 

the Manager’s approval letter must 

specifically reference this AD. 

(2) Accomplish the inspections and 

preventive modification of the floor beams by 

doing all the actions in accordance with Part 

3.B.2. or Part 3.B.3. of the service bulletin, as 

applicable. If any crack is found during any 

inspection, before further flight, repair as 

required by paragraph (h)(1) of this AD. 

(i) If no crack is found during any 

inspection required by paragraph (g) of this 

AD: Accomplish the actions required by 

either paragraph (i)(1) or (i)(2) of this AD, at 

the time specified. 

(1) Before further flight: Accomplish the 

inspections and preventive modification of 

the floor beam by doing all the actions in 

accordance with Part 3.B.2 or Part 3.B.3. of 

the service bulletin, as applicable. If the 

preventive modification is performed 

concurrently with the inspections required 

by paragraph (g) of this AD, the upper chord 

straps must be removed when performing the 

open-hole HFEC inspection. If any crack is 

found during any inspection, before further 

flight, repair as required by paragraph (h)(1) 

of this AD. 

(2) Before the accumulation of 20,000 total 

flight cycles, or within 1,000 flight cycles 

after the effective date of this AD, whichever 

is later: Accomplish the inspections and 

preventive modification of the upper deck 

floor beams, by doing all the actions in 

accordance with Part 3.B.2. or 3.B.3. of the 

service bulletin, as applicable. If any crack is 

found during any inspection, before further 

flight, repair as required by paragraph (h)(1) 

of this AD.

Post-Modification Inspections 

(j) Within 15,000 flight cycles after 

accomplishing the applicable preventive 

modification required by paragraph (h)(2), 

(i)(1), or (i)(2) of this AD: Accomplish the 

inspections required by either paragraph 

(j)(1) or (j)(2) of this AD; if any crack is found 

during any inspection, before further flight, 

repair as required by paragraph (h)(1) of this 

AD. 

(1) Accomplish detailed and surface HFEC 

inspections for cracking of the web, upper 

chord, and upper chord strap of the upper 

deck floor beams, by doing all the applicable 

actions in accordance with Part 3.B.4. of the 

service bulletin. If no crack is found, repeat 

the inspections at intervals not to exceed 

1,000 flight cycles. 

(2) Accomplish detailed and open-hole 

HFEC inspections for cracking of the web, 

upper chord, and strap of the upper deck 

floor beams, by doing all the applicable 

actions in accordance with Part 3.B.5. of the 

service bulletin. If no crack is found, repeat 

the inspections at intervals not to exceed 

5,000 flight cycles.

Note 2: There is no terminating action 

currently available for the repetitive 

inspections required by this AD.

Alternative Methods of Compliance 

(AMOCs) 

(k)(1) The Manager, Seattle ACO, 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 

(l) You must use Boeing Alert Service 

Bulletin 747–53A2443, dated May 9, 2002, 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. To get copies of the service 

information, contact Boeing Commercial 

Airplanes, P.O. Box 3707, Seattle, 

Washington 98124–2207. To view the AD 

docket, go to the Docket Management 

Facility, U.S. Department of Transportation, 

400 Seventh Street SW., room PL–401, Nassif 

Building, Washington, DC. To review copies 

of the service information, go to the National 

Archives and Records Administration 

(NARA). For information on the availability 

of this material at the NARA, call (202) 741–

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

federal_register/code_of_federal_regulations/

ibr_locations.html.

Issued in Renton, Washington, on June 10, 

2005. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 05–12002 Filed 6–21–05; 8:45 am] 

BILLING CODE 4910–13–P