7932 Federal Register / Vol. 62, No. 35 / Friday, February 21, 1997 / Rules and Regulations

CAUTION:

Do not attempt to overpower the autopilot.

When the autopilot is engaged, applying

force to the column may allow the alternate

trim to reposition the stabilizer. If the force

is applied long enough, it will result in an

out-of-trim condition.’’

‘‘AUTOTHROTTLE:

If the Autothrottle (A/T) disconnects when

either throttle disconnect button is

depressed, and re-engages when throttle

disconnect button is released, accomplish the

following procedures:

PROCEDURE: Use Autothrottle System (as

desired)

WHEN A DISCONNECT IS NECESSARY:

AUTOTHROTTLE RELEASE

BUTTON PRESS AND HOLD

• Press and hold either button until

flashing red A/T annunciation is illuminated.

Flashing red light indicates autothrottle is

disconnected.

• AUTOTHROTTLE RELEASE BUTTON

may then be released.

• The FMA A/T window will annunciate

as though the A/T is engaged.

• The flashing red A/T annunciation of the

FMA cannot be extinguished with repeated

depression of the autothrottle release button.

• If the throttle levers are retarded to the

idle stop, the flashing red A/T annunciation

will extinguish, and the A/T system will reengage.

• If the DFGC is selected to the IAS mode

and the A/T SPEED mode is selected, the A/

T system will re-engage.’’

(c) Within 12 months after the effective

date of this AD, accomplish the inspection

and replacement of the autopilot and

autothrottle engage switches in the flight

guidance control panel (FGCP), in

accordance with the paragraphs 3., 3.A., and

3.B. of the Accomplishment Instructions of

McDonnell Douglas Service Bulletin MD80–

22–122, dated August 6, 1996 (for Model DC–

9–80 series airplanes and Model MD–88

airplanes); and McDonnell Douglas Service

Bulletin MD90–22–005, dated August 6, 1996

(for Model MD–90 airplanes). Once these

actions are completed, the AFM revision

required by paragraphs (a) and (b) of this AD

may be removed.

Note 2: The McDonnell Douglas service

bulletins referenced in this paragraph refer to

Honeywell Incorporated Service Bulletin

4034242–22–13 for additional service

instructions.

(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, Los

Angeles 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, Los Angeles ACO.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Los Angeles ACO.

(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.

(f) The actions shall be done in accordance

with McDonnell Douglas Service Bulletin

MD80–22–122, dated August 6, 1996 (for

Model DC–9–80 series airplanes and Model

MD–88 airplanes); and McDonnell Douglas

Service Bulletin MD90–22–005, dated August

6, 1996 (for Model MD–90 airplanes). 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

McDonnell Douglas Corporation, 3855

Lakewood Boulevard, Long Beach, California

90846, Attention: Technical Publications

Business Administration, Department C1–

L51 (2–60). Copies may be inspected at the

FAA, Transport Airplane Directorate, 1601

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

the FAA, Transport Airplane Directorate, Los

Angeles Aircraft Certification Office, 3960

Paramount Boulevard, Lakewood, California;

or at the Office of the Federal Register, 800

North Capitol Street, NW., suite 700,

Washington, DC.

(g) This amendment becomes effective on

March 28, 1997.

Issued in Renton, Washington, on February

10, 1997.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–3844 Filed 2–20–97; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 96–ANE–15; Amendment 39–

9927; AD 97–04–04]

RIN 2120–AA64

Airworthiness Directives; AlliedSignal

Inc. GTCP85 Series Auxiliary Power

Units

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to AlliedSignal Inc. (formerly

Garrett Auxiliary Power Division)

GTCP85 Series auxiliary power units

(APUs), that currently requires

removing the existing turbine wheel

shroud and installing one constructed of

Hastelloy ‘‘S’’ material, or installing a

containment augmentation ring. This

amendment deletes the option of

installing a turbine shroud constructed

of Hastelloy ‘‘S’’ material. This

amendment is prompted by a report of

insufficient APU containment capability

with the Hastelloy ‘‘S’’ shroud alone

installed. The actions specified by this

AD are intended to prevent turbine

shroud fragments from exiting the APU

and puncturing the APU compartment,

which could result in reduced fire

extinguishing capability in the APU

compartment.

DATES: Effective March 24, 1997.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of March 24,

1997.

ADDRESSES: The service information

referenced in this AD may be obtained

from AlliedSignal Aerospace, Attn: Data

Distribution, M/S 64–3/2101–201, P.O.

Box 29003, Phoenix, AZ 85038–9003;

telephone (602) 365–2493, fax (602)

365–5577. This information may be

examined at the Federal Aviation

Administration (FAA), New England

Region, Office of the Assistant Chief

Counsel, 12 New England Executive

Park, Burlington, MA 01803–5299; or at

the Office of the Federal Register, 800

North Capitol Street, NW., suite 700,

Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Robert Baitoo, Aerospace Engineer, Los

Angeles Aircraft Certification Office,

FAA, Transport Airplane Directorate,

3960 Paramount Blvd., Lakewood, CA

90712–4137; telephone (310) 627–5245;

fax (310) 627–5210.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39)

by superseding AD 93–07–13,

Amendment 39–8545 (58 FR 21917,

April 26, 1993), which is applicable to

AlliedSignal Inc. (formerly Garrett

Auxiliary Power Division) GTCP85

Series auxiliary power units (APUs),

was published in the Federal Register

on August 12, 1996 (61 FR 41751). That

action proposed to require installing an

improved containment augmentation

ring, Part Number (P/N) 3616426–1, or

P/N 3616426–3, which is a redesigned

containment augmentation ring to allow

installation on certain APUs that cannot

accept the ¥1 containment

augmentation ring. The containment

augmentation rings, P/Ns 3616426–1

and 3616426-3, improve the

containment capability of the APU

relative to the earlier containment

augmentation ring, P/N 3612249–1, by

preventing turbine shroud fragments

from passing around the containment

augmentation ring. The installation

must be accomplished within 24

months after the effective date of this

AD, for flight operable APUs, and

within 36 months after the effective date

of this AD, for APUs that are operable

on the ground only. The actions would

be required to be accomplished in

accordance with AlliedSignal Aerospace

Alert Service Bulletin (ASB) No.
Federal Register / Vol. 62, No. 35 / Friday, February 21, 1997 / Rules and Regulations 7933

GTCP85–49–A7189, Revision 2, dated

October 8, 1996, AlliedSignal Aerospace

ASB No. GTCP85–49–A7189, Revision

1, dated July 19, 1996, or AlliedSignal

Aerospace ASB No. GTCP85–49–A7189,

Original, dated March 29, 1996; and

AlliedSignal Aerospace ASB No.

GTCP85–49–A6706, Revision 2, dated

November 28, 1994, AlliedSignal

Aerospace ASB No. GTCP85–49–A6706,

Revision 1, dated November 12, 1993, or

Garrett ASB No. GTCP85–49–A6706,

Original, dated December 7, 1992.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comments received.

One commenter states that the AD

should apply only to APUs with onepiece cast turbine wheels made of

MAR–M–247 material, as only these

type turbine wheels have failed in the

commenter’s experience. The FAA

concurs in part. The proposed rule as

written applies to APUs with one-piece

cast turbine wheels with the listed P/Ns,

which are made of MAR–M–247

material, but also Inconel, which have

failed as well.

Two commenters state that the AD

should add an additional method of

compliance by replacing the one-piece

cast turbine wheels with two-piece

wheels. The FAA does not concur. The

proposed AD does not apply to APUs

with two-piece turbine wheels.

One commenter (the manufacturer)

states that the economic analysis

provides figures for the number of APUs

in service domestically and worldwide

that are too low. The FAA concurs and

revised the economic analysis of this

final rule accordingly.

One commenter states that the

proposed AD should be more clear in

stating that compliance is acceptable

with either ASB stated in paragraphs

(a)(1) and (a)(2) and (b)(1) and (b)(2) of

the compliance section. The FAA

concurs and has put the ‘‘or’’ between

the appropriate paragraphs in bold type

to highlight its significance.

Two commenters concur with the AD

as proposed.

Since publication of the proposed

rule, AlliedSignal Aerospace has issued

Revision 2 to ASB No. GTCP85–49–

A7189, dated October 8, 1996, which is

referenced in this final rule along with

Revision 1, dated July 19, 1996, and

Original, dated March 29, 1996. These

revisions of that ASB are all approved

methods of compliance for the

appropriate paragraphs of this AD.

After careful review of the available

data, including the comments noted

above, the FAA has determined that air

safety and the public interest require the

adoption of the rule with the changes

described previously. The FAA has

determined that these changes will

neither increase the economic burden

on any operator nor increase the scope

of the AD.

There are approximately 4,100 APUs

of the affected design in the worldwide

fleet. The FAA estimates that 1,300

APUs installed on aircraft of U.S.

registry will be affected by this AD, that

it will take no additional work hours if

the required actions are accomplished

when the APU is already disassembled

in the shop. Required parts will cost

approximately $1,550 per APU. Based

on these figures, the total cost impact of

the AD on U.S. operators is estimated to

be $2,015,000.

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, 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 39–8545 (52 FR

45163, November 25, 1987) and by

adding a new airworthiness directive,

Amendment 39–9927, to read as

follows:

97–04–04 AlliedSignal Inc.: Amendment

39–9927. Docket 96–ANE–15.

Supersedes AD 93–07–13, Amendment

39–8545.

Applicability: AlliedSignal Inc. (formerly

Garrett Auxiliary Power Division) GTCP85

series auxiliary power units (APUs),

incorporating a one-piece cast turbine wheel,

Part Numbers (P/Ns) 968095–X, 3604604–X,

3606982–1, or 3842072–X (where ‘‘X’’

denotes any number). These APUs are

installed on but not limited to the following

aircraft: British Aerospace BAC 1–11 series;

Boeing 707, 727, and 737 series; Lockheed

L382 series; and McDonnell Douglas DC–8–

70, DC–9, and MD–88 series aircraft.

Note 1: This airworthiness directive (AD)

applies to each APU 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 APUs 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 (c)

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 turbine shroud fragments from

exiting the APU and puncturing the APU

compartment, which could result in reduced

fire extinguishing capability in the APU

compartment, accomplish the following:

(a) For flight operable APUs, within 24

months after the effective date of this AD,

accomplish either of the following:

(1) Install a containment augmentation

ring, P/N 3616426–3, in accordance with

AlliedSignal Aerospace Alert Service

Bulletin (ASB) No. GTCP85–49–A7189,

Revision 2, dated October 8, 1996, Revision

1, dated July 19, 1996, or Original, dated

March 29, 1996; or

(2) Install a containment augmentation

ring, P/N 3616426–1, in accordance with

AlliedSignal Aerospace ASB No.GTCP85–

49–A6706, Revision 2, dated November 28,

1994, AlliedSignal Aerospace ASB No.

GTCP85–49–A6706, Revision 1, dated

November 12, 1993, or Garrett ASB No.

GTCP85–49–A6706, Original, dated

December 7, 1992.

(b) For APUs that are operable on the

ground only, within 36 months after the

effective date of this AD, accomplish either

of the following:

(1) Install a containment augmentation

ring, P/N 3616426–3, in accordance with

AlliedSignal Aerospace ASB No. GTCP85–
7934 Federal Register / Vol. 62, No. 35 / Friday, February 21, 1997 / Rules and Regulations

49–A7189, Revision 2, dated October 8, 1996,

Revision 1, dated July 19, 1996, or Original,

dated March 29, 1996; or

(2) Install a containment augmentation

ring, P/N 3616426–1, in accordance with

AlliedSignal Aerospace ASB No. GTCP85–

49–A6706, Revision 2, dated November 28,

1994, AlliedSignal Aerospace ASB No.

GTCP85–49–A6706, Revision 1, dated

November 12, 1993, or Garrett ASB No.

GTCP85–49–A6706, Original, dated

December 7, 1992.

(c) 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, Los

Angeles Aircraft Certification Office. The

request should be forwarded through an

appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, Los Angeles Aircraft

Certification Office.

Note 2: Information concerning the

existence of approved alternative method of

compliance with this AD, if any, may be

obtained from the Los Angeles Aircraft

Certification Office.

(d) 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 aircraft to

a location where the requirements of this AD

can be accomplished.

(e) The actions required by this AD shall

be done in accordance with the following

ASBs:

Document No. Pages Revision Date

AlliedSignal Aerospace, GTCP85–49–A7189 .............................................................................. 1–14 ........ 2 ....................... Oct. 8, 1996.

Total pages: 14.

AlliedSignal Aerospace, GTCP85–49–A7189 .............................................................................. 1–12 ........ 1 ....................... July 19, 1996.

Total pages: 12.

AlliedSignal Aerospace, GTCP85–49–A7189 .............................................................................. 1–10 ........ Original ............. Mar. 29, 1996.

Total pages: 10.

AlliedSignal Aerospace, GTCP85–49–A6706 .............................................................................. 1 .............. 2 ....................... Nov. 28, 1994.

2, 3 .......... 1 ....................... Nov. 12, 1993.

4 .............. 2 ....................... Nov. 28, 1994.

5–8 .......... 1 ....................... Nov. 12, 1993.

9, 10 ........ 2 ....................... Nov. 28, 1994.

Total pages: 10.

AlliedSignal Aerospace GTCP85–49–A6706 1–10 ........ 1 ....................... Nov. 12, 1993

Total pages: 10.

Garrett GTCP85–49–A6706 ......................................................................................................... 1, 2 .......... Original ............. Dec. 7, 1992

4–10 ........ Original ............. Dec. 7, 1992.

Total pages: 9.

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 AlliedSignal Aerospace, Attn: Data

Distribution, M/S 64–3/2101–201, P.O. Box

29003, Phoenix, AZ 85038–9003; telephone

(602) 365–2493, fax (602) 365–5577. Copies

may be inspected at the FAA, New England

Region, Office of the Assistant Chief Counsel,

12 New England Executive Park, Burlington,

MA; or at the Office of the Federal Register,

800 North Capitol Street, NW., Suite 700,

Washington, DC.

(f) This amendment becomes effective on

March 24, 1997.

Issued in Burlington, Massachusetts, on

February 4, 1997.

James C. Jones,

Acting Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 97–4098 Filed 2–20–97; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 97–NM–30–AD; Amendment

39–9939; AD 97–04–14]

RIN 2120–AA64

Airworthiness Directives; Aerospatiale

Model ATR42–200, –300, and –320

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 certain Aerospatiale Model

ATR42–200, –300, and –320 series

airplanes. This action requires

modification of the electrical wiring of

the stick pusher/shaker test function to

reinforce system protection. This

amendment is prompted by a report of

at least one occurrence when the stick

pusher self-activated during flight. The

actions specified in this AD are

intended to prevent inadvertent

activation of the stick pusher, which

could cause reduced controllability of

the airplane, especially during takeoff or

landing.

DATES: Effective March 10, 1997.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of March 10,

1997.

Comments for inclusion in the Rules

Docket must be received on or before

April 22, 1997.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 97–NM–

30–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

The service information referenced in

this AD may be obtained from

Aerospatiale, 316 Route de Bayonne,

31060 Toulouse, Cedex 03, 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: Gary

Lium, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(206) 227–1112; fax (206) 227–1149.

SUPPLEMENTARY INFORMATION: The

Direction Ge ́ne ́rale de l’Aviation Civile

(DGAC), which is the airworthiness

authority for France, recently notified

the FAA that an unsafe condition may

exist on certain Model ATR42–200,

–300, and –320 series airplanes. The

DGAC advises of at least one occurrence

of the inadvertent activation of the stick

pusher test function. An electrical fault

could be the cause of this anomaly;

however, at this time, the exact cause is

not known. This condition, if not

corrected, could result in self-activation

of the stick pusher during flight, which

would cause reduced controllability of

the airplane, especially during takeoff or

landing.