18238 Federal Register / Vol. 61, No. 81 / Thursday, April 25, 1996 / Rules and Regulations

(B) If only one spring pin is installed,

install a second spring pin.

(C) Reinstall the trimming panel.

(D) Reinstall the door.

(E) Install the snapwire as specified in

paragraph (a)(1)(i) of this AD.

(2) If a door jettison handle shaft is not

locked to the jettison system, before further

flight, accomplish the following.

(i) Remove the door and the trimming

panel.

(ii) Remove the sheared spring pin.

(iii) Replace the sheared spring pin with

two spring pins.

(iv) Reinstall the door trimming panels.

(v) Reinstall the door.

(vi) Install the snapwire as described in

paragraph (a)(1)(i) of this AD.

Note 2: Eurocopter Service Bulletin SA

365, No. 01.38, dated January 31, 1994,

pertains to this AD.

(b) An alternative method of compliance or

adjustment of the compliance time that

provides an acceptable level of safety may be

used when approved by the Manager,

Rotorcraft Standards Staff, FAA, Rotorcraft

Directorate. Operators shall submit their

requests through an FAA Principal

Maintenance Inspector, who may concur or

comment and then send it to the Manager,

Rotorcraft Standards Staff.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Rotorcraft Standards Staff.

(c) 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 helicopter

to a location where the requirements of this

AD can be accomplished.

(d) This amendment becomes effective on

May 30, 1996.

Issued in Fort Worth, Texas, on April 18,

1996.

Eric Bries,

Acting Manager, Rotorcraft Directorate,

Aircraft Certification Service.

[FR Doc. 96–10075 Filed 4–24–96; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 96–NM–75–AD; Amendment

39–9581; AD 96–09–07]

Airworthiness Directives; Boeing

Model 757 Series Airplanes Equipped

With Moog Spoiler Actuators

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD)

that is applicable to Boeing Model 757

series airplanes equipped with certain

Abex spoiler actuator electro-hydraulic

servo valves (EHSV) installed in certain

spoiler actuators. The existing AD

currently requires a one-time inspection

of the spoiler actuator to determine if a

suspect EHSV is incorrectly installed,

and replacement of the EHSV, if

necessary. That amendment was

prompted by reports that a bias spring

in the EHSV of certain spoiler actuators

was found to be incorrectly installed.

The actions specified by that AD are

intended to prevent a significant control

upset of the airplane as a result of

problems associated with an incorrectly

installed EHSV in the spoiler actuator

assembly. This amendment adds

additional suspect EHSV’s that require

inspection; it also corrects the actuator

manufacturer’s name and corrects the

serial number of one EHSV.

DATES: Effective May 10, 1996.

Comments for inclusion in the Rules

Docket must be received on or before

June 24, 1996.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 96–NM–

75–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Information concerning this AD

action may be examined at the FAA,

Transport Airplane Directorate, 1601

Lind Avenue, SW., Renton, Washington.

FOR FURTHER INFORMATION CONTACT: Don

Eiford, Aerospace Engineer, Systems

and Equipment Branch, ANM–130S,

FAA, Seattle Aircraft Certification

Office, 1601 Lind Avenue, SW., Renton,

Washington; telephone (206) 227–2788;

fax (206) 227–1181.

SUPPLEMENTARY INFORMATION: On March

5, 1996, the FAA issued AD 96–06–01,

amendment 39–9537 (61 FR 9607,

March 11, 1996), which is applicable to

Boeing Model 757 series airplanes

equipped with certain electro hydraulic

servo valves (EHSV) installed in certain

spoiler actuators. That AD requires a

one-time inspection of the EHSV on the

spoiler actuator to determine if a

suspect valve is incorrectly installed; if

so, the EHSV must be replaced. That

action was prompted by reports that a

bias spring in the EHSV of certain

spoiler actuators was found to be

incorrectly installed.

If the jet pipe in the first stage of the

EHSV is plugged, or if the differential

pressure between the extend and retract

ports pressurized by the jet pipe is

inadequate, an incorrectly installed bias

spring on the second stage spool would

cause the spoiler to be driven into the

‘‘deploy’’ position. Such inadvertent

spoiler deployment would result in the

airplane experiencing a rolling moment.

If the airplane is already banked or is at

a low altitude, or if the crew does not

respond rapidly enough to control the

uncommanded roll, a significant control

upset of the airplane could result. The

actions required by AD 96–06–01 are

intended to prevent the occurrence of

such a control upset.

New Data Since Issuance of AD 96–06–

01

Since the issuance of that AD, the

manufacturer has provided the FAA

with data indicating that additional

suspect EHSV’s may be installed on the

affected airplanes. These suspect

EHSV’s have serial numbers of 595, 563,

and 909. If any these EHSV’s are

installed on an airplane, there is the

potential for the occurrence of the same

unsafe condition that was addressed by

AD 96–06–01.

Explanation of New AD

Since an unsafe condition has been

identified that is likely to exist or

develop on other airplanes of this same

type design, this AD supersedes AD 96–

06–01 to require a one-time inspection

of the spoiler actuator to determine if a

suspect EHSV is incorrectly installed,

and replacement of the EHSV, if

necessary. This AD requires the

inspection for and removal of three

additional suspect EHSV’s.

Additionally, action is taken

throughout this AD to specify the

correct names of the manufacturers of

the spoiler actuator and the EHSV. The

subject spoiler actuators are

manufactured by Moog; the subject

EHSV’s are manufactured by Abex.

Table 1 of this AD has been corrected

to indicate that the order numbers are

‘‘Abex’’ order numbers, rather than

‘‘Boeing’’ order numbers.

Due to a typographical error, EHSV

serial number ‘‘559’’ was incorrectly

listed in Table 1 of AD 96–06–01 as

serial number ‘‘569.’’ This AD corrects

that error.

Cost Impact

According to the records of the EHSV

manufacturer, all of the affected EHSV’s

were shipped to be installed on Model

757 series airplanes that currently are

operated by non-U.S. operators under

foreign registry. None of the Model 757

series airplanes affected by this action

are on the U.S. Register; therefore, they

are not directly affected by this AD

action. However, the FAA considers that

this rule is necessary to ensure that the

unsafe condition is addressed in the

event that:

1. any of the subject airplanes are

imported and placed on the U.S.

Register in the future; or
Federal Register / Vol. 61, No. 81 / Thursday, April 25, 1996 / Rules and Regulations 18239

2. any one of the suspect EHSV’s is

installed on a U.S.-registered airplane in

the the future.

Should an affected airplane be placed

on the U.S. Register in the future, it

would require approximately 1 work

hour to accomplish the required actions,

at an average labor charge of $60 per

work hour. Based on these figures, the

cost impact of this AD would be $60 per

airplane.

Conclusion

Since this AD action does not affect

any airplane that is currently on the

U.S. register, it has no adverse economic

impact and imposes no additional

burden on any person. Therefore, notice

and public procedures hereon are

unnecessary and the amendment may be

made effective in less than 30 days after

publication in the Federal Register.

Comments Invited

Although this action is in the form of

a final rule and was not preceded by

notice and opportunity for public

comment, comments are invited on this

rule. Interested persons are invited to

comment on this 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 under the caption

ADDRESSES. All communications

received on or before the closing date

for comments will be considered, and

this rule may be amended in light of the

comments received. Factual information

that supports the commenter’s ideas and

suggestions is extremely helpful in

evaluating the effectiveness of the AD

action and determining whether

additional rulemaking action would be

needed.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the rule that might suggest a need to

modify the 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 that

summarizes each FAA-public contact

concerned with the substance of this AD

will be filed in the Rules Docket.

Commenters wishing the FAA to

acknowledge receipt of their comments

submitted in response to this rule must

submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 96–NM–75–AD.’’ The

postcard will be date stamped and

returned to the commenter.

The regulations adopted herein will

not have substantial direct effects 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, in

accordance with Executive Order 12612,

it is determined that this final rule does

not have sufficient federalism

implications to warrant the preparation

of a Federalism Assessment.

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, 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 39–9537 (61 FR

9607, March 11, 1996), and by adding a

new airworthiness directive (AD),

amendment 39–9581, to read as follows:

96–09–07 Boeing: Amendment 39–9581.

Docket 96–NM–75–AD. Supersedes AD

96–06–01, Amendment 39–9537.

Applicability: Model 757 airplanes,

certificated in any category, that are

equipped with Moog spoiler actuators having

Abex electro-hydraulic servo valves (EHSV),

part number 72196, with the serial numbers

listed in Table 1 of this AD:

TABLE 1

EHSV

serial No.

Abex order

No.* Shipment Date *

AH–0001 C716657 8 November 1991.

AH–0002 C716657 8 November 1991.

TABLE 1—Continued

EHSV

serial No.

Abex order

No.* Shipment Date *

AH–0003 C727995 25 August 1994.

AH–0004 C727995 25 August 1994.

AH–0005 C727995 25 August 1995.

AH–0006 C727995 25 August 1995.

AH–0007 C727995 25 August 1995.

13 ............ C731181 12 June 1995.

49 ............ C730878 01 June 1995.

61 ............ C727955 13 September

1994.

131 .......... C708905 13 November 89.

233 .......... C727730 17 June 1994.

241 .......... C731540 13 September

1995.

260 .......... C727955 13 September

1994.

279 .......... C728298 02 September

1994.

275 .......... C727880 24 June 1994.

308 .......... C725421 01 December 1993.

329 .......... C727711 17 June 1994.

347 .......... C727518 14 June 1994.

401 .......... C728298 05 September

1994.

407 .......... C727730 17 June 1994.

427 .......... C731181 03 July 1995.

450 .......... C731181 03 July 1995.

445 .......... C706627 22 February 89.

457 .......... C731663 12 September

1995.

456 .......... C728887 28 November 1994.

463 .......... C731435 21 August 1995.

484 .......... C727748 22 June 1994.

515 .......... C727745 24 June 1994.

559 .......... C728290 05 September

1994.

563 .......... C724224 14 September

1993.

579 .......... C724176 14 September

1993.

595 .......... C727735 24 January 1994.

611 .......... C727955 14 September

1994.

607 .......... C727997 20 July 1994.

647 .......... C728459 10 October 1994.

726 .......... C731096 04 September

1995.

725 .......... C729525 19 December 1994.

819 .......... C728135 03 August 1994.

890 .......... C726803 06 April 1994.

874 .......... C730890 26 April 1995.

909 .......... C724877 29 November 1993.

912 .......... C727977 04 August 1994.

991 .......... C713602 10 December 1990.

998 .......... C731477 4 September 1995.

1022 ........ C708905 13 November 1989.

1023 ........ C708905 13 November 1989.

1072 ........ C709166 14 November 1989.

1148 ........ C730192 13 March 1995.

1175 ........ C723278 05 August 1993.

1227 ........ C728303 31 August 1994.

1283 ........ C731833 04 September

1995.

1487 ........ C728549 04 October 1994.

1655 ........ C728442 28 November 1994.

1780 ........ C726757 06 April 1994.

1807 ........ C728669 29 September

1994.

1862 ........ C727625 17 June 1994.

1929 ........ C727977 04 August 1994.

1986Z ...... C727730 17 June 1994.

2017Z ...... C725411 24 November 1993.
18240 Federal Register / Vol. 61, No. 81 / Thursday, April 25, 1996 / Rules and Regulations

TABLE 1—Continued

EHSV

serial No.

Abex order

No.* Shipment Date *

2034 ........ C727730 17 June 1994.

2073 ........ C731272 12 September

1995.

2125 ........ C725713 12 January 1994.

2220 ........ C729735 29 March 1995.

2334 ........ C727730 17 June 1994.

2348 ........ C727730 17 June 1994.

2426 ........ C731623 12 July 1995.

* The Abex Order Number and Shipment

Date are included in this listing to enable operators to review their records in order to determine if a suspect EHSV has been ordered,

and if, or where, it has been installed on an

airplane.

Note 1: This AD applies to each airplane

identified in the preceding applicability

provision, regardless of whether it has been

modified, altered, or repaired in the area

subject to the requirements of this AD. For

airplanes that have been modified, altered, or

repaired so that the performance of the

requirements of this AD is affected, the

owner/operator must request approval for an

alternative method of compliance in

accordance with paragraph (b) of this AD.

The request should include an assessment of

the effect of the modification, alteration, or

repair on the unsafe condition addressed by

this AD; and, if the unsafe condition has not

been eliminated, the request should include

specific proposed actions to address it.

Compliance: Required as indicated, unless

accomplished previously.

To prevent a significant control upset of

the airplane due to problems associated with

incorrectly assembled Abex electro-hydraulic

servo valves (EHSV) on certain Moog spoiler

actuators, accomplish the following:

(a) Within 6 months after the effective date

of this AD, perform the following procedure:

(1) While the airplane is on the ground,

extend the flaps to 40 degrees. and visually

inspect the spoiler actuator EHSV assembly

to determine the location of the second stage

bias spring end cap assembly.

(2) If the second stage bias spring cap

assembly is on the aft or lower side of the

EHSV assembly, prior to further flight,

replace the EHSV, having Abex part number

72196, with a serviceable unit in accordance

with the airplane maintenance manual.

Note 2: To be correctly positioned, the

second stage bias spring cap assembly should

be on the upper or forward side of the EHSV

assembly. Appendix 1 of this AD provides a

visual representation of the correct

positioning of the EHSV assembly.

(b) 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, Seattle

Aircraft Certification Office (ACO), FAA,

Transport Airplane Directorate. Operators

shall submit their requests through an

appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, Seattle ACO.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Seattle ACO.

(c) 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.

(d) This amendment becomes effective on

May 10, 1996.

Billing Code 4910–13–P
Federal Register / Vol. 61, No. 81 / Thursday, April 25, 1996 / Rules and Regulations 18241

Appendix 1
18242 Federal Register / Vol. 61, No. 81 / Thursday, April 25, 1996 / Rules and Regulations

Issued in Renton, Washington, on April 19,

1996.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 96–10209 Filed 4–24–96; 8:45 am]

BILLING CODE 4910–13–C

14 CFR Part 39

[Docket No. 96–NM–74–AD; Amendment

39–9582; AD 96–01–04 R1]

Airworthiness Directives; Saab Model

SAAB SF340A and SAAB 340B Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment revises an

existing airworthiness directive (AD),

applicable to certain Saab Model SAAB

SF340A and SAAB 340B series

airplanes, that currently requires

revising the Airplane Flight Manual

(AFM) to require verification that the

auto-ignition system is operational; to

define icing conditions at higher

ambient temperatures; and to provide

the flight crew with limitations and

procedures to aid in the avoidance of

engine power interruptions. The actions

specified by that AD are intended to

prevent failure of the auto-ignition

system to re-light the engine in the

event of power interruptions due to the

ingestion of ice and/or slush into the

engine, which could result in engine

flameout and subsequent shutdown, and

to provide the flight crew with guidance

to aid in avoidance of such occurrences.

This amendment clarifies certain

requirements of the AFM revision. This

amendment is prompted by

communications received from affected

operators that certain of the current

requirements of the AD are unclear.

DATES: Effective May 10, 1996.

Comments for inclusion in the Rules

Docket must be received on or before

June 24, 1996.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 96–NM–

74–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

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:

Ruth E. Harder, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(206) 227–1721; fax (206) 227–1149.

SUPPLEMENTARY INFORMATION: On

January 2, 1996, the FAA issued

airworthiness directive (AD) 96–01–04,

amendment 39–9480 (61 FR 511,

January 8, 1996), which is applicable to

certain Saab Model SAAB SF340A and

SAAB 340B series airplanes. That AD

requires revising the FAA-approved

Airplane Flight Manual (AFM) to:

1. Require verification that the autoignition system is operational;

2. Define icing conditions at higher

ambient temperatures; and

3. Povide the flight crew with

limitations and procedures to aid in the

avoidance of engine power

interruptions.

That AD action was prompted by a

report of complete power loss of the left

engine and power fluctuations on the

right engine as a result of build up of ice

and/or slush in the engine inlet and

subsequent ingestion into the engines.

The actions required by that AD are

intended to prevent failure of the autoignition system to re-light the engine in

the event of power interruptions due to

the ingestion of ice and/or slush into the

engine, which could result in engine

flameout and subsequent shutdown, and

to provide the flight crew with guidance

to aid in avoidance of such occurrences.