24216 Federal Register / Vol. 61, No. 94 / Tuesday, May 14, 1996 / Rules and Regulations

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 USC 106(g), 40113, 44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

removing amendment 39–8247 (57 FR

19249, May 5, 1992), and by adding a

new airworthiness directive (AD),

amendment 39–9614, to read as follows:

92–10–13 R1 McDonnell Douglas:

Amendment 39–9614. Docket 95–NM–

127–AD. Revises AD 92–10–13,

Amendment 39–8247.

Applicability: Model DC–9–80 series

airplanes and Model MD–88 airplanes

equipped with digital flight guidance

computers (DFGC) having part numbers prior

to 4034241–972; certificated in any category.

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 (d) 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 automatic thrust lever advance

on a surging engine during takeoff, which

could cause engine failure, accomplish the

following:

(a) Within 30 days after May 20, 1992 (the

effective date of AD 92–10–13, amendment

39–8247), revise the Limitations Section of

the FAA-approved Airplane Flight Manual

(AFM) to include the following statement.

This may be accomplished by inserting a

copy of this AD in the AFM.

‘‘LIMITATIONS SECTION

Autothrottles must be disconnected if

engine surge (stall) is detected during

takeoff.’’

(b) Within 30 days after May 20, 1992 (the

effective date of AD 92–10–13, amendment

39–8247), revise the Procedures Section of

the FAA-approved AFM to include the

following statement. This may be

accomplished by inserting a copy of this AD

in the AFM.

‘‘PROCEDURES SECTION

CAUTION

During takeoff, the Digital Flight Guidance

Computer (DFGC) engine failure logic is

armed if (1) the flight director pitch axis is

in takeoff mode, (2) the aircraft is above 400

feet radio altitude, and (3) both engine

pressure ratios (EPRs) are below the goaround EPR limit. If the DFGC detects an EPR

drop greater than or equal to 0.25 EPR and

7% N1 from the same engine, as compared to

the other engine, the engine failure logic is

satisfied and the DFGC will change the

Thrust Rating Panel (or indicator) thrust limit

to Go-Around (GA). This will cause the

autothrottle system to unclamp and enter

normal EPR limit (EPR LIM) mode where the

throttles will maintain the higher engine EPR

at the selected go-around thrust rating EPR

LIM. Such an EPR and N1 drop may also

result from an engine surge (stall). Advancing

thrust levers on a surging engine will hinder

surge recovery and may result in eventual

engine failure.

If an engine surge (stall) is detected during

takeoff:

(1) Disconnect autothrottles.

(2) Reduce thrust on affected engine (idle if

necessary).

(3) Shut down the affected engine if surging

and popping continues.

(4) If affected engine surging or popping

stops, accomplish the following:

A. Place ignition switch to GRD START &

CONTIN.

B. Place ENG anti-ice switches to ON.

C. Place PNEU X-FEED VALVE lever OPEN

on affected side.

D. Place AIR FOIL anti-ice switches ON.

E. Advance affected throttle slowly.

(5) If engine surging or popping returns, turn

the ENG anti-ice switch OFF.

(6) After normal operation has been

established, the autothrottles may be reengaged.

Note: A NO MODE light may be

annunciated due to abnormal bleed

configuration.’’

(c) Replacement of both DFGC’s having a

part number prior to 4034241–972, with

DFGC’s having part number 4034241–972, in

accordance with McDonnell Douglas Service

Bulletin MD80–22–111, dated May 23, 1995,

constitutes terminating action for the

requirements of this AD. Once the

replacements are accomplished, the AFM

revisions required by paragraphs (a) and (b)

of this AD may be removed.

Note 2: McDonnell Douglas Service

Bulletin MD80–22–111, dated May 23, 1995,

references Honeywell Service Bulletin

4034241–22–44, dated May 22, 1995, as an

additional source of service information.

Note 3: Paragraph 1.B of McDonnell

Douglas Service Bulletin MD80–22–111,

dated May 23, 1995, specifies certain

concurrent actions that affect airplanes

equipped with DFGC’s having part numbers

prior to 4034241–971.

(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 4: 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 replacement shall be done in

accordance with McDonnell Douglas Service

Bulletin MD80–22–111, dated May 23, 1995.

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, Los Angeles Aircraft Certification

Office, Transport Airplane Directorate, 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

June 13, 1996.

Issued in Renton, Washington, on May 6,

1996.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 96–11823 Filed 5–13–96; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 95–NM–95–AD; Amendment

39–9617; AD 96–10–10]

RIN 2120–AA64

Airworthiness Directives; Jetstream

Model 4101 Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Jetstream Model

4101 airplanes, that requires inspections

of the handrail assembly at the main

entrance door to detect loose or missing

rivets, abnormal movement between the

handrail pivot-tube and the spigot that

attaches to the bearing assembly, and
Federal Register / Vol. 61, No. 94 / Tuesday, May 14, 1996 / Rules and Regulations 24217

cracks on the handrail pivot-tube. It also

requires repair or replacement of the

assembly, if necessary, and provides for

two optional terminating actions. This

amendment is prompted by a report

indicating that fatigue cracks and loose

rivets were found on the handrail

assembly of the main passenger

entrance door on an in-service airplane.

The actions specified by this AD are

intended to prevent these conditions,

which can lead to the failure of the door

handrail assembly; such failure could

allow the door to fall free and

subsequently cause injury to people on

the airplane or on the ground.

DATES: Effective June 18, 1996.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of June 13,

1996.

ADDRESSES: The service information

referenced in this AD may be obtained

from Jetstream Aircraft, Inc., P.O. Box

16029, Dulles International Airport,

Washington, DC 20041–6029. 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:

William Schroeder, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(206) 227–2148; fax (206) 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 Jetstream

Model 4101 airplanes was published in

the Federal Register on November 24,

1995 (60 FR 58023). That action

proposed to require inspections of the

handrail assembly at the main entrance

door to detect loose or missing rivets,

abnormal movement between the

handrail pivot-tube and the spigot that

attaches to the bearing assembly, and

cracks on the handrail pivot-tube. It also

proposed to require repair or

replacement of the assembly, if

necessary. The proposal also provided

for two optional terminating actions.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comments received.

Support for the Proposal

Two commenters support the

proposal.

Request to Withdraw the Proposal as

Unnecessary

One commenter requests that the

proposal be withdrawn. This

commenter, the only U.S. operator

affected by the requirements of the

proposed rule, states that it is currently

in the process of accomplishing the

terminating actions on all of its affected

airplanes. Its schedule calls for the

terminating action to be accomplished

on all of these airplanes by the time the

final rule would become effective. In

light of this, the commenter maintains

that an AD is unnecessary and the

proposal should be withdrawn.

The FAA does not concur. While the

operator’s fleet may be the only

airplanes currently on the U.S. Register

that would be affected by the AD, there

is the possibility that other airplanes of

this same type design may be imported

in the future and placed on the Register.

Without this AD, there would be no

assurance that the unsafe condition was

addressed on those airplanes. For this

reason, the FAA finds that the issuance

of the final rule is both necessary and

warranted.

Conclusion

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 as proposed.

Cost Impact

The FAA estimates that 4 airplanes of

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

To accomplish the inspections, it would

take approximately 1 work hour per

airplane, at an average labor rate of $60

per work hour. Based on these figures,

the cost impact of the proposed AD on

U.S. operators is estimated to be $240,

or $60 per airplane, per inspection.

This cost impact figure 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.

However, the FAA has been advised

that the terminating actions provided by

this rule have been accomplished on all

4 affected U.S.-registered airplanes.

Therefore, the promulgation of this AD

will impose no new additional costs on

U.S. operators.

Should an operator elect to

accomplish one of the two terminating

actions provided by this AD, the

following costs would apply:

Installation of the interim

reinforcement of the handrail assembly

takes approximately 4.5 work hours to

accomplish, at an average labor charge

of $60 per work hour. Based on these

figures, the cost impact of this optional

action is $270 per airplane, plus the cost

of necessary parts.

Installation of the structural

improvements of the door and door

support, and the completely redesigned

door handrail assembly, takes

approximately10 work hours to

accomplish, at an average labor charge

of $60 per work hour. Based on these

figures, the cost impact of this optional

action is $600 per airplane, plus the cost

of necessary parts.

Regulatory Impact

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 USC 106(g), 40113, 44701.
24218 Federal Register / Vol. 61, No. 94 / Tuesday, May 14, 1996 / Rules and Regulations

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

96–10–10 Jetstream: Amendment 39–9617.

Docket 95–NM–95–AD.

Applicability: Model 4101 airplanes;

equipped with handrail assembly, Part No.

6020203 Issue C, with Modification No.

JM41179 (reference Jetstream Alert Service

Bulletin J41–A52–009); certificated in any

category.

Note 1: This AD applies to each airplane

identified in the preceding applicability

provision, regardless of whether it has been

otherwise 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 (f) 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 failure of the entrance door

handrail assembly, which subsequently

could result in injury to passengers,

flightcrew, or groundcrew, accomplish the

following:

(a) Within 50 landings after the effective

date of this AD, conduct a detailed visual

inspection of the handrail assembly at the

main entrance door to detect loose or missing

rivets, abnormal movement between the

handrail pivot-tube and the spigot that

attaches to the bearing assembly, and cracks

on the handrail pivot-tube, in accordance

with Jetstream Alert Service Bulletin J41–

A52–036, dated June 13, 1994.

(b) If no cracks or other discrepancies are

detected during the inspection required by

paragraph (a) of this AD, repeat the

inspection thereafter at intervals not to

exceed 300 hours time-in-service.

(c) If evidence of any loose or missing rivet

is revealed, or if abnormal movement

between the handrail pivot-tube and the

spigot that attaches to the bearing assembly

is detected, as a result of any of the

inspections required by this AD, prior to

further flight, accomplish the procedures

specified in paragraph 2.B.(4) of Jetstream

Alert Service Bulletin J41–A52–036, dated

June 13, 1994. Thereafter, repeat the

inspection required by paragraph (a) of this

AD at intervals not to exceed 300 hours timein-service.

(d) If evidence of cracking is revealed as a

result of any of the inspections required by

this AD, prior to further flight, accomplish

the requirements of either paragraph (d)(1),

(d)(2), or (d)(3) of this AD:

(1) Install a new handrail assembly, Part

No. 6020203 Issue C standard, as specified in

paragraph 2.B.(5)(d) of Jetstream Alert

Service Bulletin J41–A52–036, dated June 13,

1994. After installation, repeat the inspection

required by paragraph (a) of this AD at

intervals not to exceed 300 hours time-inservice. Or

(2) Install the interim reinforcement of the

handrail assembly (Customer Option Kit. No.

Jk42619) in accordance with Jetstream

Service Bulletin J41–52–041–42619, dated

June 13, 1994. Such installation constitutes

terminating action for the inspections

required by this AD. Or

Note 2: Jetstream Service Bulletin J41–52–

041–42619 refers to Flight Refuelling Service

Bulletin 6020303–52–1 for additional

installation information.

(3) Install the structural improvements of

the door and door support, and the

completely redesigned door handrail

assembly, in accordance with Jetstream

Service Bulletin J41–52–025, dated February

11, 1994. Such installation constitutes

terminating action for the inspections

required by this AD.

Note 3: Jetstream Service Bulletin J41–52–

025 refers to Flight Refuelling Service

Bulletin 6020303–52–2 for additional

installation information.

(e) Terminating action for the inspections

required by this AD consists of installation of

the item(s) specified in either paragraph

(e)(1) or (e)(2) of this AD:

(1) Installation of the interim reinforcement

of the handrail assembly (Customer Option

Kit. No. Jk42619) in accordance with

Jetstream Service Bulletin J41–52–041–

42619, dated June 13, 1994. Or

(2) Installation of the structural

improvements of the door and door support,

and the completely redesigned door handrail

assembly, in accordance with Jetstream

Service Bulletin J41–52–025, dated February

11, 1994.

(f) 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,

Standardization Branch, ANM–113, 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, Standardization

Branch, ANM–113.

Note 4: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Standardization Branch,

ANM–113.

(g) 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.

(h) The inspections shall be done in

accordance with Jetstream Alert Service

Bulletin J41–A52–036, dated June 13, 1994.

The interim reinforcement of the handrail

assembly shall be done in accordance with

Jetstream Service Bulletin J41–52–041–

42619, dated June 13, 1994. The installation

of the structural improvements of the door

and door support, and the completely

redesigned door handrail assembly, shall be

done in accordance with Jetstream Service

Bulletin J41–52–025, dated February 11,

1994. 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 Jetstream Aircraft, Inc., P.O. Box 16029,

Dulles International Airport, Washington, DC

20041–6029. 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.

(i) This amendment becomes effective on

June 18, 1996.

Issued in Renton, Washington, on May 7,

1996.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 96–11882 Filed 5–13–96; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 96–SW–01–AD; Amendment

39–9616; AD 96–06–12]

RIN 2120–AA64

Airworthiness Directives; Bell

Helicopter Textron, Inc. Model 47B,

47B–3, 47D, 47D–1, 47G, 47G–2, 47G–

2A, 47G–2A–1, 47G–3, 47G–3B, 47G–

3B–1, 47G–3B–2, 47G–3B–2A, 47G–4,

47G–4A, 47G–5, 47G–5A, 47H–1, 47J,

47J–2, 47J–2A, and 47–K Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This document publishes in

the Federal Register an amendment

adopting Airworthiness Directive (AD)

96–06–12 which was sent previously to

all known U.S. owners and operators of

Bell Helicopter Textron, Inc. (Bell)

Model 47B, 47B–3, 47D, 47D–1, 47G,

47G–2, 47G–2A, 47G–2A–1, 47G–3,

47G–3B, 47G–3B–1, 47G–3B–2, 47G–

3B–2A, 47G–4, 47G–4A, 47G–5, 47G–

5A, 47H–1, 47J, 47J–2, 47J–2A, and 47–

K helicopters by individual letters. This

AD requires a visual inspection of each

tail rotor blade (blade) tip, abrasion

strip, blade skin, and blade butt for

corrosion or delamination. This

amendment is prompted by reports that

a number of Model 47 helicopter blades

were manufactured using a clad

aluminum alloy material instead of a

bare aluminum alloy material. The

actions specified by this AD are

intended to prevent premature

delamination or separation of the blade

tip block or the abrasion strip, which

could lead to failure of the blade and

subsequent loss of control of the

helicopter.