Federal Register / Vol. 69, No. 28 / Wednesday, February 11, 2004 / Rules and Regulations 6547

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:

2004–03–28 Bombardier, Inc. (Formerly de 

Havilland, Inc.): Amendment 39–13472. 

Docket 2002–NM–79–AD.

Applicability: Model DHC–8–102, –103, 

–106, –201, –202, –301, –311, and –315 

airplanes; serial numbers 003 through 580 

inclusive; certificated in any category. 

Compliance: Required as indicated, unless 

accomplished previously. 

To prevent separation of the screws in the 

autopilot clutch assembly of the SM–300 

servo, which could result in uncommanded 

engagement of the autopilot servo and 

consequent reduced controllability of the 

airplane, accomplish the following: 

One-Time Inspection/Follow-on Corrective 

Action, if Necessary 

(a) Within 12 months after the effective 

date of this AD: Do a general visual 

inspection to determine the serial numbers of 

the elevator and aileron servo drive 

assemblies of the automatic flight control 

system per paragraphs III.1. and III.2. of the 

Accomplishment Instructions of Bombardier 

Alert Service Bulletin A8–22–18, Revision 

‘B’, dated November 19, 2001.

Note 1: 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.’’

(1) If any elevator or aileron servo, part 

number (P/N) 7002260–922, or any aileron 

servo, P/N 7002260–923, with serial numbers 

4826 through 5935 inclusive, is found: Before 

further flight, do all the follow-on actions per 

paragraphs III.3. and III.4. of the 

Accomplishment Instructions of Bombardier 

Alert Service Bulletin A8–22–18, Revision 

‘‘B’’, dated November 19, 2001; and per 

paragraphs 3.A. through 3.F. of the 

Honeywell Accomplishment Instructions 

specified on pages 14 through 17 of the 

Bombardier service bulletin. 

(2) If no serial number specified in 

paragraph (a)(1) of this AD is found, no 

further action is required by this paragraph. 

Part Installation 

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

person may install an elevator or aileron 

servo, P/N 7002260–922, or an aileron servo, 

P/N 7002260–923, with serial numbers 4826 

through 5935 inclusive, on any airplane.

Note 2: Although Bombardier Alert Service 

Bulletin A8–22–18, Revision ‘‘B’’, dated 

November 19, 2001, specifies 

accomplishment of concurrent requirements, 

this AD does not include those requirements.

Alternative Methods of Compliance 

(c) In accordance with 14 CFR 39.19, the 

Manager, New York Aircraft Certification 

Office, FAA, is authorized to approve 

alternative methods of compliance for this 

AD. 

Incorporation by Reference 

(d) The actions shall be done in accordance 

with Bombardier Alert Service Bulletin A8–

22–18, Revision ‘B’, dated November 19, 

2001. 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 Regional Aircraft Division, 

123 Garratt Boulevard, Downsview, Ontario 

M3K 1Y5, Canada. Copies may be inspected 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue, SW., Renton, 

Washington; or at the FAA, New York 

Aircraft Certification Office, 1600 Stewart 

Avenue, Westbury, New York; or at the 

Office of the Federal Register, 800 North 

Capitol Street, NW., suite 700, Washington, 

DC.

Note 3: The subject of this AD is addressed 

in Canadian airworthiness directive CF–

2001–40, dated November 9, 2001.

Effective Date 

(e) This amendment becomes effective on 

March 17, 2004.

Issued in Renton, Washington, on February 

3, 2004. 

Ali Bahrami, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–2681 Filed 2–11–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2001–NM–284–AD; Amendment 

39–13469; AD 2004–03–25] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A330 and A340–200 and –300 Series 

Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a 

new airworthiness directive (AD), 

applicable to certain Airbus Model 

A330 and A340–200 and –300 series 

airplanes, that requires repetitive 

inspections for proper installation of the 

parachute pins located in the escape 

slides/rafts at the door 3 Type I 

emergency exits on the left and right 

sides of the airplane; a one-time 

inspection of the associated electrical 

harnesses for the escape slides/rafts for 

proper routing and installation; and 

corrective actions if necessary. This AD 

also requires adjustment of the speed 

lacing for the soft covers of the escape 

slides/rafts, which will terminate the 

repetitive inspections. This action is 

necessary to prevent failure of the 

escape slides/rafts to deploy correctly at 

door 3 Type I emergency exits, which 

could result in the escape slides/rafts 

being unusable during an emergency 

evacuation, and consequent injury to 

passengers or crew members. This 

action is intended to address the 

identified unsafe condition.

DATES: Effective March 17, 2004. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of March 17, 

2004.

ADDRESSES: The service information 

referenced in this AD may be obtained 

from Airbus, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France. 

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: Tim 

Backman, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–2797; 

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 Airbus 

Model A330 and A340–200 and –300 

series airplanes was published in the 

Federal Register on December 5, 2003 

(68 FR 67984). That action proposed to 

require repetitive inspections for proper 

installation of the parachute pins 

located in the escape slides/rafts at the 

door 3 Type I emergency exits on the 

left and right sides of the airplane; a 

one-time inspection of the associated 

electrical harnesses for the escape 

slides/rafts for proper routing and 

6548 Federal Register / Vol. 69, No. 28 / Wednesday, February 11, 2004 / Rules and Regulations 

installation; and corrective actions if 

necessary. That action also proposed to 

require adjustment of the speed lacing 

for the soft covers of the escape slides/

rafts, which would terminate the 

repetitive inspections. 

Comments 

Interested persons have been afforded 

an opportunity to participate in the 

making of this amendment. Due 

consideration has been given to the one 

comment received. 

Request To Clarify Paragraph (c), Parts 

Installation 

The commenter states that the 

affected slide part numbers and serial 

number range are listed in the 

Applicability section of the proposed 

AD, but only the affected part numbers 

are listed in paragraph (c), Parts 

Installation, of the proposed AD. The 

commenter requests that the serial 

number range be included in paragraph 

(c) to coincide with the Applicability 

section. The commenter states that this 

change would clarify that slide/raft 

assemblies with serial numbers later 

than those in the applicability section 

are not affected by the AD. 

The FAA concurs with the 

commenter’s request to add the serial 

number range which appears in the 

Applicability section of this final rule to 

paragraph (c). We find that this change 

will clarify that slide/raft assemblies 

with serial numbers later than those 

listed in paragraph (c) are not affected 

by this final rule. We have clarified 

paragraph (c) of this final rule 

accordingly. 

Conclusion 

After careful review of the available 

data, including the comment noted 

above, we have determined that air 

safety and the public interest require the 

adoption of the rule with the change 

described previously. We have 

determined that this change will neither 

increase the economic burden on any 

operator nor increase the scope of the 

AD. 

Cost Impact 

We estimate that 14 Model A330 

series airplanes of U.S. registry will be 

affected by this AD, that it will take 

approximately 1 work hour per airplane 

to accomplish the required inspections, 

and that the average labor rate is $65 per 

work hour. Based on these figures, the 

cost impact on U.S. operators of the 

inspections required by this AD is 

estimated to be $910, or $65 per 

airplane. 

It will take approximately 3 work 

hours per airplane to adjust the speed 

lacing for the escape slide/raft soft cover 

at an average labor rate of $65 per work 

hour. Based on these figures, the cost 

impact on U.S. operators for the 

adjustment of the speed lacing for the 

escape slide/raft soft cover required by 

this AD is estimated to be $2,730, or 

$195 per airplane. 

The cost impact figures discussed 

above are 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. 

Currently, there are no Model A340 

series airplanes on the U.S. Register. 

However, should an affected airplane be 

imported and placed on the U.S. 

Register in the future, it will require 1 

work hour per airplane to accomplish 

the inspections and 3 work hours per 

airplane to accomplish the adjustment 

of the speed lacing for the escape slide/

raft soft cover, at an average labor rate 

of $65 per work hour. Based on these 

figures, the cost impact of the AD for 

Model A340 operators would be $260 

per airplane. 

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:

2004–03–25 Airbus: Amendment 39–13469. 

Docket 2001–NM–284–AD.

Applicability: Model A330 and A340–200 

and –300 series airplanes equipped with an 

escape slide/raft having any part number (P/

N) 7A1509–101 through 7A1509–117 

inclusive, and any serial number AD001 

through AD0855 inclusive, at door 3 Type I 

emergency exits; certificated in any category. 

Compliance: Required as indicated, unless 

accomplished previously. 

To prevent failure of the escape slides/rafts 

to deploy correctly at door 3 Type I 

emergency exits, which could result in the 

escape slides/rafts being unusable during an 

emergency evacuation, and consequent 

injury to passengers or crew members, 

accomplish the following: 

Inspections 

(a) Within 550 flight hours after the 

effective date of this AD: Do a detailed 

inspection of the escape slides/rafts located 

at door 3 Type I emergency exits, on the left 

and right sides of the airplane, for correct 

installation of the parachute pins, and a onetime detailed inspection of the associated 

electrical harnesses for correct installation of 

the quick-disconnect connector, in 

accordance with paragraphs 4.1 and 4.2 of 

Airbus All Operator Telex (AOT) A330–

25A3154 (for Model A330 series airplanes) or 

A340–25A4172 (for Model A340–200 and 

–300 series airplanes), both dated July 26, 

2001; as applicable. If any parachute pin or 

quick disconnect connector is incorrectly 

installed, before further flight, do the 

corrective actions per the applicable AOT. 

Repeat the inspections of the parachute pins 

thereafter at intervals not to exceed 1,000 

flight hours until accomplishment of 

paragraph (b) of this AD.

Note 1: For the purposes of this AD, a 

detailed inspection is defined as: ‘‘An 

intensive visual examination of a specific 

structural area, system, installation, or 

assembly to detect damage, failure, or 

irregularity. Available lighting is normally 

supplemented with a direct source of good 

lighting at intensity deemed appropriate by 

Federal Register / Vol. 69, No. 28 / Wednesday, February 11, 2004 / Rules and Regulations 6549

the inspector. Inspection aids such as mirror, 

magnifying lenses, etc., may be used. Surface 

cleaning and elaborate access procedures 

may be required.’’

Note 2: Repetitive inspections of the 

electrical harnesses are not required.

Terminating Action for Repetitive 

Inspections 

(b) Within 18 months after the effective 

date of this AD: Adjust the speed lacing for 

the soft covers of the escape slides/rafts 

located at door 3 Type I emergency exits, in 

accordance with paragraph 4.3 of Airbus 

AOT A330–25A3154 (for Model A330 series 

airplanes) or A340–25A4172 (for Model 

A340–200 and –300 series airplanes), both 

dated July 26, 2001; as applicable. This 

adjustment terminates the repetitive 

inspections of the parachute pins required by 

paragraph (a) of this AD.

Note 3: The AOTs reference Goodrich 

Aircraft Evacuation Systems Alert Service 

Bulletin 7A1509–25A324, dated July 16, 

2001, as an additional source of service 

information for adjusting the speed lacing.

Parts Installation 

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

person may install on any airplane an escape 

slide/raft having any P/N 7A1509–101 

through 7A1509–117 inclusive, and any 

serial number AD001 through AD0855 

inclusive, unless the parachute pin has been 

inspected and the speed lacing has been 

adjusted in accordance with paragraphs (a) 

and (b) of this AD. 

Alternative Methods of Compliance 

(d) In accordance with 14 CFR 39.19, the 

Manager, International Branch, ANM–116, 

FAA, Transport Airplane Directorate, is 

authorized to approve alternative methods of 

compliance for this AD. 

Incorporation by Reference 

(e) The actions shall be done in accordance 

with Airbus All Operator’s Telex A330–

25A3154, dated July 26, 2001; or Airbus All 

Operator’s Telex A340–25A4172, dated July 

26, 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 Airbus, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France. 

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 4: The subject of this AD is addressed 

in French airworthiness directives 2001–

359(B) R3, dated October 30, 2002, and 2001–

360(B) R1, dated February 6, 2002.

Effective Date 

(f) This amendment becomes effective on 

March 17, 2004.

Issued in Renton, Washington, on February 

3, 2004. 

Ali Bahrami, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–2682 Filed 2–10–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2003–NM–223–AD; Amendment 

39–13468; AD 2004–03–24] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A330–200, A330–300, A340–200, and 

A340–300 Series Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule; request for 

comments. 

SUMMARY: This amendment adopts a 

new airworthiness directive (AD) that is 

applicable to all Airbus Model A330–

200, A330–300, A340–200, and A340–

300 series airplanes. This action 

requires a revision of the airplane flight 

manual to include procedures for a preflight elevator check before each flight, 

repetitive inspections for cracks of the 

attachment lugs of the mode selector 

valve position transducers on the 

elevator servocontrols, and corrective 

actions if necessary. This action is 

intended to advise the flightcrew of the 

potential for an undetected inoperative 

elevator, and of the action they must 

take to avoid this hazard. This action is 

necessary to ensure proper functioning 

of the elevator surfaces, and to detect 

and correct cracking of the attachment 

lugs, which could result in partial loss 

of elevator function and consequent 

reduced controllability of the airplane. 

This action is intended to address the 

identified unsafe condition.

DATES: Effective February 26, 2004. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of February 

26, 2004. 

Comments for inclusion in the Rules 

Docket must be received on or before 

March 11, 2004.

ADDRESSES: Submit comments in 

triplicate to the Federal Aviation 

Administration (FAA), Transport 

Airplane Directorate, ANM–114, 

Attention: Rules Docket No. 2003–NM–

223–AD, 1601 Lind Avenue, SW., 

Renton, Washington 98055–4056. 

Comments may be inspected at this 

location between 9 a.m. and 3 p.m., 

Monday through Friday, except Federal 

holidays. Comments may be submitted 

via fax to (425) 227–1232. Comments 

may also be sent via the Internet using 

the following address: 9-anmiarcomment@faa.gov. Comments sent 

via the Internet must contain ‘‘Docket 

No. 2003–NM–223–AD’’ in the subject 

line and need not be submitted in 

triplicate. Comments sent via fax or the 

Internet as attached electronic files must 

be formatted in Microsoft Word 97 or 

2000 or ASCII text. 

The service information referenced in 

this AD may be obtained from Airbus, 

1 Rond Point Maurice Bellonte, 31707 

Blagnac Cedex, France. This 

information may be examined 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.

FOR FURTHER INFORMATION CONTACT: Tim 

Backman, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–2797; 

fax (425) 227–1149.

SUPPLEMENTARY INFORMATION: The 

Direction Ge ́ne ́rale de l’Aviation Civile 

(DGAC), which is the airworthiness 

authority for France, notified the FAA 

that an unsafe condition may exist on 

all Airbus Model A330–200, A330–300, 

A340–200, and A340–300 series 

airplanes. Each elevator on these 

airplanes is equipped with two 

servocontrols having three operating 

modes. A selector valve installed in 

each servocontrol enables the 

servocontrol to change between 

operating modes; the selector valve’s 

position is transmitted to the flight 

control computers by a transducer. The 

DGAC advises that several cracks of the 

transducer body at its attachment lugs 

have been detected. The affected 

transducers were installed at the 

damping positions 3CS1 and 3CS2. The 

cracks resulted in displacement of the 

transducer and consequent leakage of 

the hydraulic fluid into the affected 

servocontrol. In two cases the 

displacement of the transducer resulted 

in the elevator becoming inoperative (it 

dropped into a full down position), with 

no electronic centralized aircraft 

monitor (ECAM) warning provided to 

the flightcrew. Without an ECAM 

warning, this inoperative condition can 

be identified only if no elevator surface 

movement is detected during a preflight elevator check. Loss of elevator 

function, if not corrected, could result