Federal Register / Vol. 69, No. 25 / Friday, February 6, 2004 / Proposed Rules 5785

Administration proposes to amend 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:

Boeing: Docket 2002–NM–151–AD.

Applicability: All Model 767–200 and –300 

series airplanes; certificated in any category.

Compliance: Required as indicated, unless 

accomplished previously. 

To prevent the actuators for the off-wing 

slide compartment door from not firing, 

which could cause the door to open 

improperly and prevent the deployment of 

the off-wing escape slide, leading to the loss 

of an evacuation route, accomplish the 

following: 

Inspection and Corrective Action 

(a) Within two years after the effective date 

of this AD, do an inspection of the actuators 

for the off-wing slide compartment door on 

the right and left sides of the airplane to 

determine the actuator cartridge serial 

number, in accordance with the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 767–25–

0299, dated January 18, 2001. 

(b) If any actuator cartridge having serial 

numbers 5481 through 5741 inclusive is 

found during the inspection required by 

paragraph (a) of this AD: Before further flight, 

perform the actions specified in paragraphs 

(b)(1) through (b)(3) of this AD in accordance 

with the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

767–25–0299, dated January 18, 2001. 

(1) Remove the actuator for the off-wing 

slide compartment door. 

(2) Perform an inspection of the actuator 

cartridge for the presence of a clearance hole 

and corrective actions if necessary (includes 

replacing the actuator cartridge with a new 

actuator cartridge or a serviceable actuator 

cartridge from a recharge kit). 

(3) Install the actuator for the off-wing slide 

compartment door.

Note 1: Boeing Special Attention Service 

Bulletin 767–25–0299, dated January 18, 

2001, references OEA Aersospace, Inc. 

Service Bulletin 5262 (02) SB (NC), dated 

October 2, 2000, as an additional source of 

service information for performing the 

inspection of the actuator cartridge and 

corrective actions.

Parts Installation 

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

person shall install an actuator for the offwing escape slide having OEA part number 

5262200 cartridge assembly with actuator 

cartridge serial numbers 5481 through 5741 

inclusive that do not have a clearance hole 

between the two firing pins, on any airplane. 

Alternative Methods of Compliance 

(d) In accordance with 14 CFR 39.19, the 

Manager, Seattle Aircraft Certification Office, 

FAA, is authorized to approve alternative 

methods of compliance for this AD.

Issued in Renton, Washington, on January 

29, 2004. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–2478 Filed 2–5–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2003–NM–83–AD] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 757 and 767 Series Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: This document proposes the 

adoption of a new airworthiness 

directive (AD) that is applicable to 

certain Boeing Model 757 and 767 series 

airplanes. This proposal would require 

inspection to determine the serial 

number of the hydraulic pump in the 

ram air turbine (RAT), and corrective 

action, if necessary. This action is 

necessary to prevent a cracked hanger 

arm of the hydraulic pump of the RAT 

that can fracture under load and lead to 

failure of the RAT to provide hydraulic 

power to the primary flight control 

system during an emergency when both 

engines have failed. Loss of hydraulic 

power to the primary flight controls 

could result in loss of control of the 

airplane. This action is intended to 

address the identified unsafe condition.

DATES: Comments must be received by 

March 22, 2004.

ADDRESSES: Submit comments in 

triplicate to the Federal Aviation 

Administration (FAA), Transport 

Airplane Directorate, ANM–114, 

Attention: Rules Docket No. 2003–NM–

83–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-anmnprmcomment@faa.gov. Comments sent 

via fax or the Internet must contain 

‘‘Docket No. 2003–NM–83–AD’’ in the 

subject line and need not be submitted 

in triplicate. Comments sent via the 

Internet as attached electronic files must 

be formatted in Microsoft Word 97 or 

2000 or ASCII text. 

The service information referenced in 

the proposed rule may be obtained from 

Boeing Commercial Airplanes, PO Box 

3707, Seattle, Washington 98124–2207. 

This information may be examined at 

the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., 

Renton, Washington.

FOR FURTHER INFORMATION CONTACT:

Kenneth Frey, Aerospace Engineer, 

Systems and Equipment Branch, ANM–

130S, FAA, Seattle Aircraft Certification 

Office, 1601 Lind Avenue, SW., Renton, 

Washington 98055–4056; telephone 

(425) 917–6468; fax (425) 917–6590.

SUPPLEMENTARY INFORMATION:

Comments Invited 

Interested persons are invited to 

participate in the making of the 

proposed rule by submitting such 

written data, views, or arguments as 

they may desire. Communications shall 

identify the Rules Docket number and 

be submitted in triplicate to the address 

specified above. All communications 

received on or before the closing date 

for comments, specified above, will be 

considered before taking action on the 

proposed rule. The proposals contained 

in this action may be changed in light 

of the comments received. 

Submit comments using the following 

format: 

• Organize comments issue-by-issue. 

For example, discuss a request to 

change the compliance time and a 

request to change the service bulletin 

reference as two separate issues. 

• For each issue, state what specific 

change to the proposed AD is being 

requested. 

• Include justification (e.g., reasons or 

data) for each request.

Comments are specifically invited on 

the overall regulatory, economic, 

environmental, and energy aspects of 

the proposed rule. All comments 

submitted will be available, both before 

and after the closing date for comments, 

in the Rules Docket for examination by 

interested persons. A report 

summarizing each FAA-public contact 

concerned with the substance of this 

proposal will be filed in the Rules 

Docket. 

Commenters wishing the FAA to 

acknowledge receipt of their comments 

submitted in response to this action 

must submit a self-addressed, stamped 

postcard on which the following 

statement is made: ‘‘Comments to 

5786 Federal Register / Vol. 69, No. 25 / Friday, February 6, 2004 / Proposed Rules 

Docket Number 2003–NM–83–AD.’’ The 

postcard will be date stamped and 

returned to the commenter. 

Availability of NPRMs 

Any person may obtain a copy of this 

NPRM by submitting a request to the 

FAA, Transport Airplane Directorate, 

ANM–114, Attention: Rules Docket No. 

2003–NM–83–AD, 1601 Lind Avenue, 

SW., Renton, Washington 98055–4056. 

Discussion 

The FAA has received a report 

indicating that some ram air turbines 

(RAT) may have hydraulic pumps with 

cracked hanger arms on certain Boeing 

Model 757 and 767 series airplanes. The 

supplier of the RATs identified a 

departure from the defined 

manufacturing process as the cause for 

production of hanger arms with 

potential surface cracks, which affects 

approximately 154 hydraulic pumps 

with certain serial numbers. A cracked 

hanger arm of the hydraulic pump of the 

RAT, if not corrected, can fracture under 

load and lead to failure of the RAT to 

provide hydraulic power to the primary 

flight control system during an 

emergency when both engines have 

failed. Loss of hydraulic power to the 

primary flight controls could result in 

loss of control of the airplane. 

Explanation of Relevant Service 

Information 

The FAA has reviewed and approved 

Boeing Special Attention Service 

Bulletin 757–29–0060, dated September 

12, 2002 (for Model 757–200, –200CB, 

and –200PF series airplanes); Boeing 

Special Attention Service Bulletin 757–

29–0061, dated September 12, 2002 (for 

Model 757–300 series airplanes); Boeing 

Special Attention Service Bulletin 767–

29–0103, dated September 12, 2002 (for 

Model 767–200, –300, and –300F series 

airplanes); and Boeing Special Attention 

Service Bulletin 767–29–0106, dated 

September 12, 2002 (for Model 767–

400ER series airplanes). 

These service bulletins describe 

procedures for inspection to determine 

the serial number of the hydraulic pump 

in the RAT, and corrective action, if 

necessary. The corrective action(s) 

includes either replacing the hydraulic 

pump with a serviceable hydraulic 

pump that is outside the range of the 

affected serial numbers, or reworking 

and reidentifying the existing hydraulic 

pump. Accomplishment of the actions 

specified in the service bulletins is 

intended to adequately address the 

identified unsafe condition. 

These service bulletins also refer to 

Parker Service Bulletin 6513902–29–

305, dated November 30, 2001, as an 

additional source of service information 

for the list of affected hydraulic pump 

serial numbers and for accomplishment 

of the reworking and reidentifying of the 

existing hydraulic pump for Model 757 

and 767 series airplanes. 

Explanation of Requirements of 

Proposed Rule 

Since an unsafe condition has been 

identified that is likely to exist or 

develop on other products of this same 

type design, the proposed AD would 

require accomplishment of the actions 

specified in the Boeing service bulletins 

described previously. 

Cost Impact 

There are approximately 1,851 

airplanes of the affected design in the 

worldwide fleet. The FAA estimates that 

1,038 airplanes of U.S. registry would be 

affected by this proposed AD. 

We estimate that it would take 

approximately 1 work hour per airplane 

to accomplish the proposed inspection, 

and that the average labor rate is $65 per 

work hour. Based on these figures, the 

cost impact of the proposed inspection 

on U.S. operators is estimated to be 

$67,470, or $65 per airplane. 

We also estimate that it would take 

approximately 4 work hours per 

airplane (affecting approximately 154 

airplanes) to accomplish the proposed 

replacement of the hydraulic pump, if 

required, and that the average labor rate 

is $65 per work hour. Based on these 

figures, the cost impact of the proposed 

replacement on U.S. operators is 

estimated to be $260 per airplane. 

We also estimate that it would take 

approximately 5 work hours per 

airplane (affecting approximately 154 

airplanes) to accomplish the proposed 

reworking and reidentification of the 

hydraulic pump, if required, and that 

the average labor rate is $65 per work 

hour. Based on these figures, the cost 

impact of the proposed reworking and 

reidentification on U.S. operators is 

estimated to be $325 per airplane. 

The cost impact figures discussed 

above are based on assumptions that no 

operator has yet accomplished any of 

the proposed requirements of this AD 

action, and that no operator would 

accomplish those actions in the future if 

this proposed 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. The 

manufacturer may cover the cost of 

replacement parts associated with this 

proposed AD, subject to warranty 

conditions. As a result, the costs 

attributable to the proposed AD may be 

less than stated above. 

Regulatory Impact 

The regulations proposed herein 

would 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 proposal 

would not have federalism implications 

under Executive Order 13132. 

For the reasons discussed above, I 

certify that this proposed regulation (1) 

is not a ‘‘significant regulatory action’’

under Executive Order 12866; (2) is not 

a ‘‘significant rule’’ under the DOT 

Regulatory Policies and Procedures (44 

FR 11034, February 26, 1979); and (3) if 

promulgated, 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 copy of the draft 

regulatory evaluation prepared for this 

action is contained in the Rules Docket. 

A copy of it may be obtained by 

contacting the Rules Docket at the 

location provided under the caption 

ADDRESSES.

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Safety.

The Proposed Amendment 

Accordingly, pursuant to the 

authority delegated to me by the 

Administrator, the Federal Aviation 

Administration proposes to amend 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:

Boeing: Docket 2003–NM–83–AD.

Applicability: Model 757–200, –200CB, 

–200PF, and –300 series airplanes, line 

numbers 1 through 998 inclusive; and Model 

767–200, –300, –300F, and –400ER series 

airplanes, line numbers 1 through 869 

inclusive; certificated in any category. 

Compliance: Required as indicated, unless 

accomplished previously.

To prevent a cracked hanger arm of the 

hydraulic pump of the ram air turbine (RAT) 

Federal Register / Vol. 69, No. 25 / Friday, February 6, 2004 / Proposed Rules 5787

that can fracture under load and lead to 

failure of the RAT to provide hydraulic 

power to the primary flight control system 

during an emergency when both engines 

have failed, which could result in loss of 

hydraulic power to the primary flight 

controls and consequent loss of control of the 

airplane; accomplish the following: 

Service Bulletin Reference 

(a) The term ‘‘service bulletin,’’ as used in 

this AD, means the Accomplishment 

Instructions of the following service bulletins 

in Table 1 of this AD, as applicable:

TABLE 1.—SERVICE BULLETINS

Molded Service bulletin Date 

Model 757–200, –200CB, and –200PF series airplanes ..... Boeing Special Attention Service Bulletin 757–29–0060 ..... September 12, 2002. 

Model 757–300 series airplanes .......................................... Boeing Special Attention Service Bulletin 757–29–0061 ..... September 12, 2002. 

Model 767–200, –300, and –300F series airplanes ............. Boeing Special Attention Service Bulletin 767–29–0103 ..... September 12, 2002. 

Model 767–400ER series airplanes ..................................... Boeing Special Attention Service Bulletin 767–29–0106 ..... September 12, 2002. 

Note 1: These service bulletins refer to 

Parker Service Bulletin 6513902–29–305, 

dated November 30, 2001, as an additional 

source of service information for the list of 

affected hydraulic pump serial numbers and 

for accomplishment of the reworking and 

reidentifying of the existing hydraulic pump 

for Model 757 and 767 series airplanes.

Inspection of Serial Number 

(b) Within 36 months after the effective 

date of this AD, do an inspection to 

determine the serial number of the hydraulic 

pump in the RAT, per the service bulletin. 

Corrective Actions 

(c) If the hydraulic pump is found to have 

an affected serial number during the 

inspection required by paragraph (b) of this 

AD, within 36 months after the effective date 

of this AD, do the corrective action(s) in 

either paragraph (c)(1) or (c)(2) of this AD. 

(1) Replace the hydraulic pump with a 

serviceable hydraulic pump that is outside 

the range of the affected serial numbers, per 

the service bulletin. 

(2) Rework and reidentify the hydraulic 

pump, per the service bulletin. 

Part Installation 

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

person shall install on any airplane a RAT 

hydraulic pump, Parker part number (P/N) 

65139–02 or Hamilton Sunstrand P/N 

5903420, with an affected serial number as 

listed in Parker Service Bulletin 6513902–

29–305, dated November 30, 2001, unless it 

has been modified per paragraph (c)(2) of this 

AD. 

Alternative Methods of Compliance 

(e) In accordance with 14 CFR 39.19, the 

Manager, Seattle Aircraft Certification Office, 

FAA, is authorized to approve alternative 

methods of compliance for this AD.

Issued in Renton, Washington, on January 

29, 2004. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–2479 Filed 2–5–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2003–NM–19–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A300 B4–600, A300 B4–600R, and A300 

F4–600R (Collectively Called A300–

600), A310, A319, A320, A321, A330, 

and A340 Series Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: This document proposes the 

adoption of a new airworthiness 

directive (AD) that is applicable to 

certain Airbus Model A300–600, A310, 

A319, A320, A321, A330, and A340 

series airplanes. This proposal would 

require a one-time inspection to 

determine if certain Thales pitot probes 

are installed, a check for certain part 

numbers and serial numbers of the 

affected pitot probes, and cleaning of 

the drain hole of any affected pitot 

probes if obstructed. This action is 

necessary to prevent obstruction of the 

air intake of the pitot probes, which 

could result in misleading information 

being provided to the flightcrew. This 

action is intended to address the 

identified unsafe condition.

DATES: Comments must be received by 

March 8, 2004.

ADDRESSES: Submit comments in 

triplicate to the Federal Aviation 

Administration (FAA), Transport 

Airplane Directorate, ANM–114, 

Attention: Rules Docket No. 2003–NM–

19–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-anmnprmcomment@faa.gov. Comments sent 

via fax or the Internet must contain 

‘‘Docket No. 2003–NM–19–AD’’ in the 

subject line and need not be submitted 

in triplicate. Comments sent via the 

Internet as attached electronic files must 

be formatted in Microsoft Word 97 or 

2000 or ASCII text. 

The service information referenced in 

the proposed rule may be obtained from 

Airbus Industrie, 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.

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: 

Comments Invited 

Interested persons are invited to 

participate in the making of the 

proposed rule by submitting such 

written data, views, or arguments as 

they may desire. Communications shall 

identify the Rules Docket number and 

be submitted in triplicate to the address 

specified above. All communications 

received on or before the closing date 

for comments, specified above, will be 

considered before taking action on the 

proposed rule. The proposals contained 

in this action may be changed in light 

of the comments received. 

Submit comments using the following 

format: 

• Organize comments issue-by-issue. 

For example, discuss a request to 

change the compliance time and a 

request to change the service bulletin 

reference as two separate issues. 

• For each issue, state what specific 

change to the proposed AD is being 

requested. 

• Include justification (e.g., reasons or 

data) for each request.