63442 Federal Register / Vol. 69, No. 211 / Tuesday, November 2, 2004 / Rules and Regulations 

Issued in Fort Worth, Texas, on October 22, 

2004. 

David A. Downey, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service.

[FR Doc. 04–24225 Filed 11–1–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39

[Docket No. 2003–SW–39–AD; Amendment 

39–13839; AD 2004–22–11] 

RIN 2120–AA64

Airworthiness Directives; Eurocopter 

Deutschland GmbH Model EC135 P1, 

P2, T1, and T2 Helicopters

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes 

an existing airworthiness directive (AD) 

for Eurocopter Deutschland GmbH 

(Eurocopter) Model EC135 P1, P2, T1, 

and T2 helicopters. That AD currently 

requires adding the AD or a statement 

to the Rotorcraft Flight Manual (RFM) 

informing the pilot to reduce power and 

land as soon as practicable if a thumplike sound followed by an unusual 

vibration occurs during flight. That AD 

also requires visually inspecting the 

main rotor drive torque strut assembly 

(strut) for a crack or a break, recording 

the inspections in the historical or 

equivalent record, re-marking and 

relocating the strut, as appropriate, and 

replacing any unairworthy strut with an 

airworthy strut. Also, that AD 

establishes life limits for certain struts 

and revises the life limit for other struts. 

This amendment requires the same 

actions as the existing AD except that it 

changes the visual inspection from a 

one-time inspection to daily 

inspections; reduces the life limit for 

aluminum struts; and eliminates the 

once-only transfer and remarking of 

certain struts. This amendment is 

prompted by an incident in which a 

pilot felt an in-flight increase in 

vibration and subsequent discovery of a 

failed strut. The actions specified by 

this AD are intended to prevent failure 

of a strut and subsequent loss of control 

of the helicopter.

DATES: Effective December 7, 2004. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of December 

7, 2004.

ADDRESSES: The service information 

referenced in this AD may be obtained 

from American Eurocopter Corporation, 

2701 Forum Drive, Grand Prairie, Texas 

75053–4005, telephone (972) 641–3460, 

fax (972) 641–3527. This information 

may be examined at the FAA, Office of 

the Regional Counsel, Southwest 

Region, 2601 Meacham Blvd., Room 

663, Fort Worth, Texas; 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.

FOR FURTHER INFORMATION CONTACT:

Richard Monschke, Aviation Safety 

Engineer, FAA, Rotorcraft Directorate, 

Rotorcraft Standards Staff, Fort Worth, 

Texas 76193–0110, telephone (817) 

222–5116, fax (817) 222–5961.

SUPPLEMENTARY INFORMATION: A 

proposal to amend 14 CFR part 39 by 

superseding AD 2003–20–11, 

Amendment 39–13329 (68 FR 58581, 

October 10, 2003), for the specified 

Eurocopter model helicopters was 

published in the Federal Register on 

June 2, 2004 (69 FR 31051). The action 

proposed to require adding the AD or a 

statement to the RFM informing the 

pilot to reduce power and land as soon 

as practicable if a thump-like sound 

followed by unusual vibration occurs 

during flight; visually inspecting the 

strut for a crack or a break before the 

first flight of each day; replacing any 

unairworthy strut with an airworthy 

strut; replacing all aluminum struts with 

titanium struts on or before 

accumulating 500 hours time-in service 

(TIS) or no later than December 31, 

2004, whichever occurs first; installing 

the struts in pairs; and canceling the 

once-only transfer and remarking of 

certain struts. 

The Luftfahrt-Bundesamt (LBA), the 

airworthiness authority for the Federal 

Republic of Germany, notified the FAA 

that an unsafe condition may exist on 

Eurocopter Model EC135 P1, P2, T1, 

and T2 helicopters. The LBA advises 

that the holders of affected aircraft 

registered in the Federal Republic of 

Germany must carry out the inspection 

for a crack, marking, replacement, and 

reduction of life limit of struts in 

accordance with the manufacturer’s 

alert service bulletin. 

Eurocopter has issued Alert Service 

Bulletin EC135–63A–002, Revision 4, 

dated July 7, 2003 (ASB), concerning 

reduction in life limit for the strut, and 

visual inspections of the strut and 

emergency stop. The ASB contains 

errors—in paragraph 1.A., the 

abbreviation ‘‘S/N’’ should be ‘‘P/N’’

and in paragraphs 1.C., 1.E.(1), and 

1.E.(2), it incorrectly states that the ASB 

is Revision 3 rather than Revision 4. The 

LBA classified this ASB as mandatory 

and issued AD No. 2001–107/3, dated 

August 21, 2003, to ensure the 

continued airworthiness of these 

helicopters in the Federal Republic of 

Germany. 

These helicopter models are 

manufactured in Germany and are type 

certificated for operation in the United 

States under the provisions of 14 CFR 

21.29 and the applicable bilateral 

agreement. Pursuant to the applicable 

bilateral agreement, the LBA has kept 

the FAA informed of the situation 

described above. The FAA has 

examined the findings of the LBA, 

reviewed all available information, and 

determined that AD action is necessary 

for products of this type design that are 

certificated for operation in the United 

States. 

Interested persons have been afforded 

an opportunity to participate in the 

making of this amendment. No 

comments were received on the 

proposal or the FAA’s determination of 

the cost to the public. The FAA has 

determined that air safety and the 

public interest require the adoption of 

the rule as proposed with only a minor 

editorial change. This change will 

neither increase the economic burden 

on any operator nor increase the scope 

of the AD. 

The FAA estimates that this AD will 

affect 50 helicopters of U.S. registry. It 

will take approximately 92.25 work 

hours per helicopter to accomplish the 

inspections and parts replacement at an 

average labor rate of $65 per work hour. 

Required parts will cost approximately 

$7,296 per helicopter. Based on these 

figures, we estimate the total cost 

impact of this AD on U.S. operators to 

be $664,612 to replace the aluminum 

struts on the entire fleet. 

The regulations adopted herein 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. Therefore, it is 

determined that this final rule does not 

have federalism implications under 

Executive Order 13132.

For the reasons discussed above, I 

certify that this action (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 

Federal Register / Vol. 69, No. 211 / Tuesday, November 2, 2004 / Rules and Regulations 63443

impact, positive or negative, on a 

substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. A final evaluation has 

been prepared for this action and it is 

contained in the Rules Docket. A copy 

of it may be obtained from the Rules 

Docket at the location provided under 

the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety.

Adoption of the Amendment

■ Accordingly, pursuant to the authority 

delegated to me by the Administrator, 

the Federal Aviation Administration 

amends part 39 of the Federal Aviation 

Regulations (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. Section 39.13 is amended by 

removing Amendment 39–13329 (68 FR 

58581, October 10, 2003), and by adding 

a new airworthiness directive (AD), 

Amendment 39–13839, to read as 

follows:

2004–22–11 Eurocopter Deutschland 

GmbH: Amendment 39–13839. Docket 

No. 2003–SW–39–AD. Supersedes AD 

2003–20–11, Amendment 39–13329, 

Docket No. 2003–SW–08–AD.

Applicability: Model EC135 P1, P2, T1, and 

T2 helicopters, with main rotor drive 

aluminum torque strut assembly (strut), part 

number (P/N) L633M1001 103 or L633M1001 

105, installed, certificated in any category. 

Compliance: Required as indicated, unless 

accomplished previously. 

To prevent failure of the strut and 

subsequent loss of control of the helicopter, 

do the following: 

(a) Before further flight, insert a copy of 

this AD or insert a statement into the 

Emergency Procedures Section of the 

Rotorcraft Flight Manual (RFM) to inform the 

pilot to reduce power and land as soon as 

practicable if a thump-like sound followed by 

an unusual vibration occurs during flight. 

(b) Before the first flight of each day, using 

a light and mirror, inspect each aluminum 

strut for a crack or a break by following the 

Accomplishment Instructions, paragraph 3.B. 

of Eurocopter Alert Service Bulletin EC135–

63A–002, Revision 4, dated July 7, 2003 

(ASB). Replace any cracked or broken strut 

with a new titanium strut, P/N L633M1001 

104, before further flight. 

(c) Within the next 100 hours time-inservice (TIS), for each aluminum strut with 

400 or more hours TIS, replace each 

aluminum strut with a titanium strut, P/N 

L633M1001 104. 

(d) This AD revises the Airworthiness 

Limitations section of the maintenance 

manual by reducing the retirement life of 

each aluminum strut, P/N L633M1001 103 

and L633M1001 105, to 500 total hours TIS 

or retiring them no later than December 31, 

2004, whichever comes first. 

(e) The aluminum struts must be replaced 

with titanium struts in pairs and at the same 

time. Installing one aluminum strut and one 

titanium strut is not authorized. After 

installing titanium struts, recalculate the 

weight and balance using 0.356kg as the 

weight and 1498.76kgmm as the moment for 

both titanium struts.

Note 1: The once-only transferring and 

remarking of certain aluminum struts 

provided in the superseded AD are no longer 

authorized.

(f) Replacing aluminum struts, P/N 

L633M1001 103 and L633M1001 105, with 

titanium struts, P/N L633M1001 104, 

constitutes terminating action for the 

requirements of this AD. Titanium struts 

have no life limit. 

(g) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Contact the Safety Management Group 

for information about previously approved 

alternative methods of compliance. 

(h) The inspections shall be done in 

accordance with Eurocopter Alert Service 

Bulletin EC135–63A–002, Revision 4, dated 

July 7, 2003. The Director of the Federal 

Register approved the incorporation by 

reference in accordance with 5 U.S.C. 552(a) 

and 1 CFR part 51. Copies may be obtained 

from American Eurocopter Corporation, 2701 

Forum Drive, Grand Prairie, Texas 75053–

4005, telephone (972) 641–3460, fax (972) 

641–3527. Copies may be inspected at the 

FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham Blvd., 

Room 663, Fort Worth, Texas; 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.

(i) This amendment becomes effective on 

December 7, 2004.

Note 2: The subject of this AD is addressed 

in Luftfahrt-Bundesamt (Federal Republic of 

Germany) AD 2001–107/3, dated August 21, 

2003.

Issued in Fort Worth, Texas, on October 22, 

2004. 

David A. Downey, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service.

[FR Doc. 04–24226 Filed 11–1–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39

[Docket No. FAA–2004–18728; Directorate 

Identifier 2003–NM–176–AD; Amendment 

39–13838; AD 2004–22–10] 

RIN 2120–AA64

Airworthiness Directives; Boeing 

Model 747–400 and –400F Series 

Airplanes

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Final rule.

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Boeing Model 747–400 and –400F series 

airplanes. This AD requires a detailed 

inspection(s) for cracks and fractures of 

the side guide support fittings in the 

lower lobe cargo compartments; and 

applicable investigative/corrective 

actions and operational limitations, if 

necessary. This AD also requires a 

terminating action for the repetitive 

inspections. This AD is prompted by 

reports of cracked/fractured side guide 

support fittings in the aft, lower lobe 

cargo compartment. We are issuing this 

AD to prevent cracked/fractured side 

guide support fittings in the lower lobe 

cargo compartments, which could result 

in unrestrained cargo shifting in flight 

and damaging the airplane structure or 

systems, and consequent reduced 

controllability of the airplane.

DATES: This AD becomes effective 

December 7, 2004. 

The incorporation by reference of 

certain publications listed in the AD is 

approved by the Director of the Federal 

Register as of December 7, 2004.

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, P.O. Box 3707, 

Seattle, Washington 98124–2207. 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 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.

FOR FURTHER INFORMATION CONTACT:

Technical information: Ivan Li,