8288 Federal Register / Vol. 60, No. 30 / Tuesday, February 14, 1995 / 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 U.S.C. App. 1354(a), 1421

and 1423; 49 U.S.C. 106(g); and 14 CFR

11.89.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding a new AD to read as follows:

95–03–02 Brackett Aircraft Company, Inc.:

Amendment 39–9139; Docket No. 94–

CE–08–AD.

Applicability: The following air filter

assemblies that utilize a neoprene gasket

incorporated in accordance with

Supplemental Type Certificate (STC)

SA71GL and installed on, but not limited to,

the following corresponding airplanes,

certificated in any category:

Air filter assembly Airplanes installed on

BA–2010 .................................................................................................... Beech Model 77 Airplanes.

BA–4106 .................................................................................................... Cessna Models 120, 140, 140A, 150, 150A, 150B, 150C, 150D, 150E,

150F, 150G, 150H, 150J, 150K, 150L, 150M, A150M, 152, and

A152; Champion Models 7ACA, 7ECA, and 7FC; Christian Industries Model Husky A–1; Luscombe Models 8, 8A, 8B, 8C, 8D, 8E,

8F, and T–8F; and Piper Models PA–22, PA–22–135, PA–22–150,

PA–22–160, PA–22–180, PA–20–115, PA–20–135, PA–38, J–3,

J3C–65, J3C–65’s, PA–11, PA–11’s, J4A, J4AS, J4E, J5A, J5A–80,

PA–12, PA–12’s, PA–16, PA–17, PA–18, PA–18A, PA–18’s, PA–

18–‘‘125’’, PA–18AS–‘‘125’’, PA–18’s–‘‘125’’, PA–18–‘‘135’’, PA–

18A–‘‘135’’, PA–18AS–‘‘135’’, and 8S–135 Airplanes.

BA–4210 .................................................................................................... Grumman American Aviation Corporation Models AA–1, AA–1A, AA–

1B, AA–1C, and AA–5 Airplanes.

BA–5110 .................................................................................................... Cessna 170, 170A, 170B, 172, 172A, 172B, 172C, 172D, 172E, 172F,

172G, 172H, 172I, 172K, 172L, and 172M; and Mooney Mite Aircraft

Corporation Model M–18C Airplanes.

BA–5110A ................................................................................................. Cessna Models 172N and 172P Airplanes.

BA–6110 .................................................................................................... Mooney Models M20, M20A, M20B, M20C, M20D, and M20G; and

Maule Models M4, M4C, M4S, M4T, M–4–220, M–4–220C, M–4–

220S, M–4–220T, M–4–180C, M–4–180S, M–4–180T, M–5–220C,

M–5–235C, M–5–180C, M–5–210TC, M–6–180, M–6–235, and M–

7–235 Airplanes.

BA–8910 .................................................................................................... Aero Commander Models 100 and 100A Airplanes.

Compliance: Required within the next 100

hours time-in-service (TIS) after the effective

date of this AD, unless already accomplished,

and thereafter at intervals not to exceed 100

hours TIS.

To prevent gasket particles from entering

the carburetor because of air filter gasket

failure, which could result in partial or

complete loss of engine power, accomplish

the following:

(a) Visually inspect the inside and outside

of the air filter frame for gasket looseness,

movement, or deterioration in accordance

with Brackett Air Filter Document I–194,

dated March 16, 1994. If any gasket

looseness, movement, or deterioration is

found, prior to further flight, accomplish the

following:

(1) Remove the air filter frame by removing

the screws, nuts, and washers on the air filter

frame (3 to 4 each) or the airlocks, as

applicable. Note that the screws securing the

grill to the frame need not be removed.

(2) Remove and replace the neoprene

gasket in accordance with Brackett Air Filter

Document 1–194. Inspect the carburetor in

accordance with the applicable maintenance

manual for gasket material ingestion. Remove

any material ingested.

(3) Reinstall the filter frame to the

carburetor heat box with the screws, nuts,

and washers (3 to 4 each) or the airlocks, as

applicable, that were earlier removed. Torque

each nut to where the neoprene gasket is

compressed to one-half its original thickness.

(b) 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.

(c) An alternative method of compliance or

adjustment of the compliance time that

provides an equivalent level of safety may be

approved by the Manager, Los Angeles

Aircraft Certification Office (ACO), FAA,

3960 Paramount Boulevard, Lakewood,

California 90712. The request shall be

forwarded through an appropriate FAA

Maintenance Inspector, who may add

comments and then send it to the Manager,

Los Angeles ACO.

Note: Information concerning the existence

of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Los Angeles ACO.

(d) The inspections required by this AD

shall be done in accordance with Brackett Air

Filter Document I–194, dated March 16,

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 the Brackett Aircraft Company, Inc.,

7045 Flightline Drive, Kingman, Arizona

86401. Copies may be inspected at the FAA,

Central Region, Office of the Assistant Chief

Counsel, Room 1558, 601 E. 12th Street,

Kansas City, Missouri, or at the Office of the

Federal Register, 800 North Capitol Street,

NW., suite 700, Washington, DC.

(e) This amendment (39–9139) becomes

effective on March 17, 1995.

Issued in Kansas City, Missouri, on January

31, 1995.

Barry D. Clements,

Manager, Small Airplane Directorate, Aircraft

Certification Service.

[FR Doc. 95–2786 Filed 2–13–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 94–SW–05–AD; Amendment

39–9149; AD 95–03–13]

Airworthiness Directives; McDonnell

Douglas Helicopter Systems and

Hughes Helicopters, Inc. Model 369

and OH–6A Series Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),
Federal Register / Vol. 60, No. 30 / Tuesday, February 14, 1995 / Rules and Regulations 8289

applicable to McDonnell Douglas

Helicopter Company and Hughes

Helicopters, Inc. Model 369 and OH–6A

series helicopters with certain main

rotor (M/R) blade assemblies or certain

M/R hub lead-lag assemblies installed,

that currently requires repetitive

inspections and checks for cracks. This

amendment requires the same

inspections as the superseded AD, but

would eliminate pilot checks, expand

the areas of inspection, and require the

application of slippage marks on each

M/R blade root fitting lug and related

bushings. This amendment is prompted

by additional reports of cracks in the M/

R blade root fittings, lugs, and adjacent

blade skin, and movement of the root

fitting bushings. The actions specified

by this AD are intended to prevent

failure of a M/R blade assembly or a M/

R hub lead-lag link assembly, loss of a

M/R blade, and subsequent loss of

control of the helicopter.

DATES: Effective March 21, 1995.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of March 21,

1995.

ADDRESSES: The service information

referenced in this AD may be obtained

from McDonnell Douglas Helicopter

Systems, Technical Publications, Bldg.

530/B111, 5000 E. McDowell Road,

Mesa, Arizona 85205–9797. This

information may be examined at the

FAA, Office of the Assistant Chief

Counsel, 2601 Meacham Blvd., Room

663, Fort Worth, Texas; or at the Office

of the Federal Register, 800 North

Capitol Street, NW., suite 700,

Washington, DC.

FOR FURTHER INFORMATION CONTACT: Mr.

Brent Bandley, Aerospace Engineer,

FAA, Los Angeles Aircraft Certification

Office, Transport Airplane Directorate,

3960 Paramount Blvd., Lakewood,

California 90712, telephone (310) 627–

5237, fax (310) 627–5210.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39)

by superseding AD 91–17–04,

Amendment 39–8003 (56 FR 42230,

August 27, 1991), which is applicable to

McDonnell Douglas Helicopter Systems

and Hughes Helicopters, Inc. Model 369

and OH–6A series helicopters with

certain main rotor (M/R) blade

assemblies or certain M/R hub lead-lag

assemblies installed, was published in

the Federal Register on July 21, 1994

(59 FR 37185). That action proposed to

require application of a slippage mark

on each M/R blade root fitting lug and

related bushings to detect movement

within 25 hours time-in-service (TIS). In

addition, that action proposed to

require, within 25 hours TIS after the

effective date of the AD and thereafter

at intervals not to exceed 100 hours TIS

from the last inspection, that the M/R

blade assembly be removed and that the

M/R blade root fittings (root fittings),

root fitting lugs, lead-lag lugs, the M/R

blade skin, and the doublers adjacent to

the root fittings be inspected for cracks.

That action also proposed that the lug

bushings be inspected for looseness and

slippage, and that slippage marks be

applied if not already present. Visual

inspections of the root fittings and M/

R lead-lag links for cracks and

inspection of the bushing slippage

marks for movement, without removing

the M/R blade, were also proposed at

intervals not to exceed 25 hours TIS.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were received on the

proposal or the FAA’s determination of

the cost to the public. The FAA has

determined that air safety and the

public interest require the adoption of

the rule as proposed except for editorial

changes and a change in the

manufacturer’s name from McDonnell

Douglas Helicopter Company to

McDonnell Douglas Helicopter Systems.

Additionally, the FAA has revised the

average labor rate from $55 per work

hour to $60 per work hour, which raises

the estimated total cost impact of the

AD to $1,320,000. The FAA has

determined that these changes will

neither increase the economic burden

on any operator nor increase the scope

of the AD.

The FAA estimates that 1,000

helicopters of U.S. registry will be

affected by this AD, that it will take

approximately 22 work hours per

helicopter to accomplish the required

actions, and that the average labor rate

is $60 per work hour. Based on these

figures, the total cost impact of the AD

on U.S. operators is estimated to be

$1,320,000.

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. App. 1354(a), 1421

and 1423; 49 U.S.C. 106(g); and 14 CFR

11.89.

§ 39.13 [Amended]

2. Section 39.13 is amended by

removing Amendment 39–8003 (56 FR

42230, August 27, 1991), and by adding

a new airworthiness directive (AD),

Amendment 39–9149, to read as

follows:

95–03–13 McDonnell Douglas Helicopter

Systems and Hughes Helicopters, Inc.:

Amendment 39–9149. Docket No. 94–

SW–05–AD. Supersedes AD 91–17–04,

Amendment 39–8003.

Applicability: Model 369 and OH–6A

series helicopters, with any of the following

parts installed: (1) Main rotor (M/R) blade

assembly (blade assembly), part number (P/

N) 369A1100–BSC, –501, –503, –505, –601,

or –603; 369D21100–BSC, –503, –505, –507,

–509, –511, –513, or –515; 369D21102–BSC

or –501; or (2) M/R hub lead-lag link

assembly (lead-lag link assembly), P/N

369A1203–BSC, –3, or –11; 369H1203–BSC,

–11, –21, or –31, certificated in any category.

Compliance: Required as indicated, unless

accomplished previously.

To prevent failure of a M/R blade assembly

or a M/R hub lead-lag link assembly, loss of

a M/R blade, and subsequent loss of control

of the helicopter, accomplish the following:

(a) Within 25 hours time-in-service (TIS)

after the effective date of this AD, and

thereafter at intervals not to exceed 100 hours

TIS from the last inspection, remove each

blade assembly from the helicopter and

accomplish the following:

(1) Inspect the attachment lugs of the M/

R blade root fittings (root fittings) and the M/
8290 Federal Register / Vol. 60, No. 30 / Tuesday, February 14, 1995 / Rules and Regulations

R lead-lag links (links) for cracks and the lug

bushings (bushings) for looseness. Conduct

the inspections in accordance with paragraph

(b) of Part I of McDonnell Douglas Helicopter

Company Service Information Notice HN–

211.4, DN–51.6, EN–42.4, FN–31.4 (SIN),

dated January 27, 1993.

(2) Visually inspect the following for

cracks—

(i) The root fittings around the blade

attachment lugs; and,

(ii) The M/R blade doubler and blade skin

adjacent to the root fittings.

(3) Mark the root fittings and bushings with

slippage marks in accordance with paragraph

(e) of Part I of the SIN, dated January 27,

1993, if the slippage marks are degraded or

missing.

(4) Replace any M/R blades or links found

to be cracked or to have loose bushings with

airworthy parts before further flight.

(b) Within 25 hours TIS after compliance

with the requirements of paragraph (a) of this

AD, and thereafter at intervals not to exceed

25 hours TIS from the last inspection,

accomplish the following without removing

the M/R blade:

(1) Visually inspect the root fittings and

links for cracks or loose bushings in

accordance with Part II of the SIN, dated

January 27, 1993.

(2) Replace any M/R blades or links found

to be cracked or to have loose bushings with

airworthy parts before further flight.

(c) 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, Los

Angeles Aircraft Certification Office, FAA.

Operators shall submit their requests through

an FAA Principal Maintenance Inspector,

who may concur or comment and then send

it to the Manager, Los Angeles Aircraft

Certification Office.

Note: Information concerning the existence

of approved alternative methods 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 helicopter

to a location where the requirements of this

AD can be accomplished.

(e) The inspections and replacements, if

necessary, shall be done in accordance with

McDonnell Douglas Helicopter Company

Service Information Notice No. HN–211.4,

DN–51.6, EN–42.4, FN–31.4, dated January

27, 1993. 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 Helicopter Systems,

Technical Publications, Bldg. 530/B111, 5000

E. McDowell Road, Mesa, Arizona 85205–

9797. Copies may be inspected at the FAA,

Office of the Assistant Chief Counsel, 2601

Meacham Blvd., Room 663, Fort Worth,

Texas; or at the Office of the Federal Register,

800 North Capitol Street, NW., suite 700,

Washington, DC.

(f) This amendment becomes effective on

March 21, 1995.

Issued in Fort Worth, Texas, on February

7, 1995.

Eric Bries,

Acting Manager, Rotorcraft Directorate,

Aircraft Certification Service.

[FR Doc. 95–3511 Filed 2–13–95; 8:45 am]

BILLING CODE 4910–13–P

14 CFR Part 39

[Docket No. 92–CE–22–AD; Amendment 39–

9124; AD 95–02–06]

Airworthiness Directives; Jetstream

Aircraft Limited (Formerly British

Aerospace, Regional Aircraft Limited)

Jetstream Model 3101 Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

Airworthiness Directive (AD) 91–08–01,

which currently requires the following

on Jetstream Aircraft Limited (JAL)

Jetstream Model 3101 airplanes: revising

the maximum speed for flaps at 50

degrees from 153/149 knots indicated

airspeed (KIAS) to 130 KIAS; and

limiting the maximum flap extension to

20 degrees anytime ice is present on the

airplane. This action requires

incorporating a flap system modification

as terminating action for the

requirements of AD 91–08–01. The

actions specified by this AD are

intended to prevent sudden pitch down

of the airplane during icing conditions,

which could lead to loss of control of

the airplane.

DATES: Effective March 10, 1995.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of March 10,

1995.

ADDRESSES: Service information that

applies to this AD may be obtained from

Jetstream Aircraft Limited, Manager

Product Support, Prestwick Airport,

Ayrshire, KA9 2RW Scotland; telephone

(44–292) 79888; facsimile (44–292)

79703; or Jetstream Aircraft Inc.,

Librarian, P.O. Box 16029, Dulles

International Airport, Washington, DC

20041–6029; telephone (703) 406–1161;

facsimile (703) 406–1469. This

information may also be examined at

the Federal Aviation Administration

(FAA), Central Region, Office of the

Assistant Chief Counsel, Room 1558,

601 E. 12th Street, Kansas City, Missouri

64106; or at the Office of the Federal

Register, 800 North Capitol Street, NW.,

suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Mr.

Raymond A. Stoer, Program Officer,

Brussels Aircraft Certification Office,

FAA, Europe, Africa, and Middle East

Office, c/o American Embassy, B–1000

Brussels, Belgium; telephone (322)

513.3830; facsimile (322) 230.6899; or

Mr. John P. Dow, Sr., Project Officer,

Small Airplane Directorate, Airplane

Certification Service, FAA, 1201

Walnut, suite 900, Kansas City, Missouri

64106; telephone (816) 426–6932;

facsimile (816) 426–2169.

SUPPLEMENTARY INFORMATION: A

proposal (supplemental notice of

proposed rulemaking) to amend part 39

of the Federal Aviation Regulations (14

CFR part 39) to include an AD that

would apply to certain JAL Model 3101

airplanes was published in the Federal

Register on October 13, 1994 (59 FR

51875). The action proposed to

supersede AD 91–08–01, Amendment

39–7007, with a new AD that would (1)

Retain the flap system operating

revision and limitation currently

required until the 35-degree flap system

modification was incorporated; and (2)

eventually require incorporating the 35-

degree flap system modification in

accordance with the instructions in

Jetstream Aircraft Limited Service

Bulletin No. 27–JA 910541, which

consists of the following pages:

Page Nos. Revision

level Date

2, 5 through 30

and 33

through 45.

Revision 1 November

11, 1991.

31 ..................... Revision 2 February 4,

1992.

1, 3, 4, and 32 .. Revision 3 November

16, 1992.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. One

comment was received in favor of the

proposal and no comments were

received concerning the FAA’s

determination of the cost to the public.

After careful review of all available

information, the FAA has determined

that air safety and the public interest

require the adoption of the rule as

proposed except for minor editorial

corrections. The FAA has determined

that these minor corrections will not

change the meaning of the AD nor add

any additional burden upon the public

than was already proposed.

The FAA estimates that 141 airplanes

in the U.S. registry will be affected by

this AD, that it will take approximately

23 workhours per airplane to

accomplish the required action, and that

the average labor rate is approximately

$55 an hour. The manufacturer will

provide parts at no cost to the owner/

operator. Based on these figures, the