Federal Register / Vol. 69, No. 6 / Friday, January 9, 2004 / Rules and Regulations 1515

To prevent peeling of the paint and 

markings from the dust covers for the flight 

data recorder (FDR) and cockpit voice 

recorder (CVR) equipment due to hydraulic 

mist from the actuators, which could result 

in the inability to identify the FDR and CVR 

equipment in the event of an accidentrecovery mission, accomplish the following: 

One-Time Inspection and Corrective Actions 

(a) For airplanes having serial numbers 

7003 through 7067 inclusive, and 7069 

through 7570 inclusive: Within 18 months 

after the effective date of this AD, do a 

general visual inspection of the dust cover for 

the FDR to determine if a chemical agent 

resistant coating has been applied to the dust 

cover. Do the inspection per Part A of the 

Accomplishment Instructions of Bombardier 

Service Bulletin 601R–31–026, dated October 

12, 2001. Dust covers that have had a 

protective coating applied are identified 

through the markings specified in the service 

bulletin. 

(1) If specified markings are present: No 

further action is required by this paragraph. 

(2) If specified markings are not present: 

Within 18 months after the effective date of 

this AD, or within 6 months after the 

inspection, whichever occurs first, do the 

action required by either paragraph (a)(2)(i) 

or (a)(2)(ii) of this AD: 

(i) Rework the FDR dust cover per Part B 

of the Accomplishment Instructions of the 

service bulletin; or 

(ii) Replace the FDR dust cover with a new 

dust cover per Part C of the Accomplishment 

Instructions of the service bulletin.

Note 2: For the purposes of this AD, a 

general visual inspection is defined as: ‘‘A 

visual examination of an interior or exterior 

area, installation, or assembly to detect 

obvious damage, failure, or irregularity. This 

level of inspection is made from within 

touching distance unless otherwise specified. 

A mirror may be necessary to enhance visual 

access to all exposed surfaces in the 

inspection area. This level of inspection is 

made under normally available lighting 

conditions such as daylight, hangar lighting, 

flashlight, or droplight and may require 

removal or opening of access panels or doors. 

Stands, ladders, or platforms may be required 

to gain proximity to the area being checked.’’

(b) For airplanes having serial numbers 

7003 through 7067 inclusive, and 7069 

through 7573 inclusive: Within 18 months 

after the effective date of this AD, do a 

general visual inspection of the CVR dust 

cover to determine if a chemical agent 

resistant coating has been applied to the dust 

cover. Dust covers that have had a protective 

coating applied are identified through the 

markings specified in the service bulletin. Do 

the inspection per Part A of the 

Accomplishment Instructions of Bombardier 

Service Bulletin 601R–23–056, dated October 

12, 2001. 

(1) If specified markings are present: No 

further action is required by this paragraph. 

(2) If specified markings are not present: 

Within 18 months after the effective date of 

this AD, or within 6 months after the 

inspection, whichever occurs first, do the 

action required by either paragraph (b)(2)(i) 

or (b)(2)(ii) of this AD: 

(i) Rework the CVR dust cover per Part B 

of the Accomplishment Instructions of the 

service bulletin; or 

(ii) Replace the CVR dust cover with a new 

dust cover per Part C of the Accomplishment 

Instructions of the service bulletin. 

Parts Installation 

(c) As of the effective date of this AD, no 

person shall install an FDR dust cover, part 

number (P/N) 074E0198–00; or a CVR dust 

cover, P/N 075E0604–00 or 9300A218S; 

unless the rework action required by 

paragraphs (a)(2)(i) and (b)(2)(i) of this AD, as 

applicable, has been done. 

Alternative Methods of Compliance 

(d) An alternative method of compliance or 

adjustment of the compliance time that 

provides an acceptable level of safety may be 

used if approved by the Manager, New York 

Aircraft Certification Office (ACO), FAA. 

Operators shall submit their requests through 

an appropriate FAA Principal Maintenance 

Inspector, who may add comments and then 

send it to the Manager, New York ACO.

Note 3: Information concerning the 

existence of approved alternative methods of 

compliance with this AD, if any, may be 

obtained from the New York ACO.

Special Flight Permits 

(e) Special flight permits may be issued in 

accordance with sections 21.197 and 21.199 

of the Federal Aviation Regulations (14 CFR 

21.197 and 21.199) to operate the airplane to 

a location where the requirements of this AD 

can be accomplished. 

Incorporation by Reference 

(f) The actions must be done in accordance 

with Bombardier Service Bulletin 601R–23–

056, dated October 12, 2001; and Bombardier 

Service Bulletin 601R–31–026, dated October 

12, 2001; as applicable. This incorporation by 

reference was approved by the Director of the 

Federal Register in accordance with 5 U.S.C. 

552(a) and 1 CFR part 51. Copies may be 

obtained from Bombardier, Inc., Canadair, 

Aerospace Group, P.O. Box 6087, Station 

Centre-ville, Montreal, Quebec H3C 3G9, 

Canada. Copies may be inspected at the FAA, 

Transport Airplane Directorate, 1601 Lind 

Avenue, SW., Renton, Washington; or at the 

FAA, New York ACO, 10 Fifth Street, Third 

Floor, Valley Stream, New York; or at the 

Office of the Federal Register, 800 North 

Capitol Street, NW., suite 700, Washington, 

DC.

Note 4: The subject of this AD is addressed 

in Canadian airworthiness directive CF–

2001–45, dated December 3, 2001.

Effective Date 

(g) This amendment becomes effective on 

February 13, 2004.

Issued in Renton, Washington, on 

December 29, 2003. 

Ali Bahrami, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–121 Filed 1–8–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2002–NM–185–AD; Amendment 

39–13425; AD 2004–01–11] 

RIN 2120–AA64 

Airworthiness Directives; Hamburger 

Flugzeugbau G.m.b.H. Model HFB 320 

HANSA Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a 

new airworthiness directive (AD), 

applicable to certain Hamburger 

Flugzeugbau G.m.b.H. Model HFB 320 

HANSA airplanes, that requires 

replacement of the elevator trim control 

cable assemblies with new assemblies. 

This action is necessary to prevent loss 

of elevator trim and possible loss of 

rudder and/or elevator function due to 

stress-corrosion cracking of certain cable 

terminals. This action is intended to 

address the identified unsafe condition.

DATES: Effective February 13, 2004. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of February 

13, 2004.

ADDRESSES: The service information 

referenced in this AD may be obtained 

from Airbus Deutschland G.m.b.H., 

Customer Service HFB 320, Mr. Dieter 

Mewes, Postfach 95 01 09, D–21111 

Hamburg, Germany. This information 

may be examined at the Federal 

Aviation Administration (FAA), 

Transport Airplane Directorate, Rules 

Docket, 1601 Lind Avenue, SW., 

Renton, Washington; or at the Office of 

the Federal Register, 800 North Capitol 

Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Dan 

Rodina, Aerospace Engineer; 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–2125; 

fax (425) 227–1149.

SUPPLEMENTARY INFORMATION: A 

proposal to amend part 39 of the Federal 

Aviation Regulations (14 CFR part 39) to 

include an airworthiness directive (AD) 

that is applicable to certain Hamburger 

Flugzeugbau G.m.b.H. Model HFB 320 

HANSA airplanes was published in the 

Federal Register on November 13, 2003 

(68 FR 64282). That action proposed to 

require replacement of the elevator trim 

control cable assemblies with new 

assemblies. 

1516 Federal Register / Vol. 69, No. 6 / Friday, January 9, 2004 / Rules and Regulations 

Comments 

The public had 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. 

Cost Impact 

The FAA estimates that 6 airplanes of 

U.S. registry will be affected by this AD, 

that it will take approximately 20 work 

hours to accomplish the replacement, 

and that the average labor rate is $65 per 

work hour. Required parts will cost 

approximately $500 per airplane. Based 

on these figures, the cost impact of the 

AD on U.S. operators is estimated to be 

$10,800, or $1,800 per airplane. 

The cost impact figure discussed 

above is based on assumptions that no 

operator has yet accomplished any of 

the requirements of this AD action, and 

that no operator would accomplish 

those actions in the future if this AD 

were not adopted. The cost impact 

figures discussed in AD rulemaking 

actions represent only the time 

necessary to perform the specific actions 

actually required by the AD. These 

figures typically do not include 

incidental costs, such as the time 

required to gain access and close up, 

planning time, or time necessitated by 

other administrative actions. 

Regulatory Impact 

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 

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 adding 

the following new airworthiness 

directive:

2004–01–11 Hamburger Flugzeugbau 

G.m.b.H.: Amendment 39–13425. Docket 

2002–NM–185–AD.

Applicability: Model HFB 320 HANSA 

airplanes, serial numbers 1023, 1027, 1030, 

1032, 1033, 1035 through 1043 inclusive, 

1045 through 1047 inclusive, 1050 through 

1055 inclusive, 1057 through 1062 inclusive, 

1064, and 1065; certificated in any category. 

Compliance: Required as indicated, unless 

accomplished previously. 

To prevent loss of elevator trim and 

possible loss of rudder and/or elevator 

function due to stress-corrosion cracking of 

certain cable terminals, accomplish the 

following: 

Replacement 

(a) Within 30 flight cycles or 2 months 

from the effective date of this AD, whichever 

occurs first, replace the elevator trim control 

cable assemblies with new assemblies in 

accordance with the Accomplishment 

Instructions of HFB 320 Hansa (Hamburger 

Flugzeugbau G.m.b.H.) Service Bulletin 27–

75, dated May 31, 2002. 

Alternative Methods of Compliance 

(b) In accordance with 14 CFR 39.19, the 

Manager, International Branch, ANM–116, 

FAA, is authorized to approve alternative 

methods of compliance for this AD. 

Incorporation by Reference 

(c) The actions must be done in accordance 

with HFB 320 Hansa (Hamburger 

Flugzeugbau G.m.b.H.) Service Bulletin 27–

75, dated May 31, 2002. This incorporation 

by reference was approved by the Director of 

the Federal Register in accordance with 5 

U.S.C. 552(a) and 1 CFR part 51. Copies may 

be obtained from Airbus Deutschland 

G.m.b.H., Customer Service HFB 320, Mr. 

Dieter Mewes, Postfach 95 01 09, D–21111 

Hamburg, Germany. Copies may be inspected 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue, SW., Renton, 

Washington; or at the Office of the Federal 

Register, 800 North Capitol Street, NW., suite 

700, Washington, DC.

Note 1: The subject of this AD is addressed 

in German airworthiness directive 2002–157, 

dated May 31, 2002.

Effective Date 

(d) This amendment becomes effective on 

February 13, 2004.

Issued in Renton, Washington, on 

December 31, 2003. 

Michael J. Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–270 Filed 1–8–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2002–NM–336–AD; Amendment 

39–13426; AD 2004–01–12] 

RIN 2120–AA64 

Airworthiness Directives; Empresa 

Brasileira de Aeronautica S.A. 

(EMBRAER) Model EMB–135 and –145 

Series Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a 

new airworthiness directive (AD), 

applicable to certain EMBRAER Model 

EMB–135 and –145 series airplanes, that 

requires operators to inspect the pitottrue air temperature (TAT) relays and 

the full authority digital engine control 

(FADEC) electronic interface resistor 

modules to detect contamination. This 

AD also requires operators to perform 

corrective action if necessary, clean the 

relay/connector pins and sockets, 

modify the seal between the cockpit 

console panels and the storm window, 

and/or install a new protective frame 

(protective sheets) at the cockpit relay 

supports. This action is necessary to 

detect and correct oxidation of the pitotTAT relay, which could result in 

increased resistance and overheating of 

the relay and consequent smoke in the 

cockpit; and to detect and correct 

oxidation of the FADEC electronic 

interface resistor modules, which could 

result in in-flight uncommanded engine 

power roll back to idle. This action is 

intended to address the identified 

unsafe condition.

DATES: Effective February 13, 2004. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of February 

13, 2004.