20016 Federal Register / Vol. 60, No. 78 / Monday, April 24, 1995 / Rules and Regulations

accordance with paragraph (b)(1) of AD 92–

16–17.

(b) Within 18 months after November 25,

1992 (the effective date of AD 92–16–17,

amendment 39–8327), inspect and modify

the escape slide compartment door latching

mechanism in accordance with Boeing Alert

Service Bulletin 767–25A0174, dated August

15, 1991. Accomplishment of the actions

required by this paragraph prior to the

effective date of this AD terminates the

actions required by paragraph (b)(2) of AD

92–16–17.

(c) Within 2 years after the effective date

of this AD, replace the currently installed

door opening actuator of the emergency offwing escape system with a new, improved

actuator, in accordance with Boeing Service

Bulletin 767–25–0216, dated February 3,

1994. Accomplishment of this replacement

terminates the repetitive inspection

requirements of paragraph (a) of this AD.

(d) As of 2 years after the effective date of

this AD, only door opening actuators of the

emergency off-wing escape system having

OEA part number 5262100 (Boeing part

number S416T208–12) shall be installed on

any airplane.

(e) 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 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Seattle ACO.

(f) 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.

(g) The replacement shall be done in

accordance with Boeing Service Bulletin

767–25–0216, dated February 3, 1994. This

incorporation by reference is approved by the

Director of the Federal Register in accordance

with 5 U.S.C. 552(a) and 1 CFR part 51. The

inspections and modification shall be done

in accordance with OEA Service Bulletin

3092100–25–002, dated July 26, 1991, and

Boeing Alert Service Bulletin 767–25A0174,

dated August 15, 1991; as applicable. The

incorporation by reference of these

documents was approved previously by the

Director of the Federal Register in accordance

with 5 U.S.C. 552(a) and 1 CFR part 51 as of

November 25, 1992 (57 FR 47987, October

21, 1992). Copies may be obtained from OEA

Aerospace, Inc., P.O. Box KK, Highway 12,

Explosive Technology Road, Fairfield,

California 94533–0659; and Boeing

Commercial Airplane Group, P.O. Box 3707,

Seattle, Washington 98124–2207. 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.

(h) This amendment becomes effective on

May 24, 1995.

Issued in Renton, Washington, on April 10,

1995.

S.R. Miller,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 95–9341 Filed 4–21–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 94–CE–30–AD; Amendment 39–

9202; AD 95–08-13]

Airworthiness Directives; B. Grob

Flugzeugbau Model G109B Gliders

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that

applies to B. Grob Flugzeugbau (Grob)

Model G109B gliders. This action

requires replacing the elevator inner

hinges with hinges of improved design.

Two occurrences where the elevator

inner hinges separated from the elevator

prompted the required action. The

actions specified by this AD are

intended to prevent failure of these

hinges because of delamination or

corrosion, which, if not detected and

corrected, could lead to loss of control

of the glider.

DATES: Effective June 2, 1995.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of June 2,

1995.

ADDRESSES: Service information that

applies to this AD may be obtained from

B. Grob Flugzeugbau, D–8939 Mattsies,

Germany. This information may also be

examined at the 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.

Herman Belderok, Project Officer,

Gliders, Small Airplane Directorate,

Aircraft Certification Service, FAA,

1201 Walnut, suite 900, Kansas City,

Missouri 64106; telephone (816) 426-

6932; facsimile (816) 426–2169.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an AD that would apply to Grob

Model G109B gliders was published in

the Federal Register on January 10,

1995 (59 FR 2555). The action proposed

to require replacing the elevator inner

hinges with hinges of improved design.

Accomplishment of the proposed action

would be in accordance with Grob

Repair Instructions No. 817–25 for

Service Bulletin TM 817–25, dated

November 9, 1987.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were received on the

proposed rule or the FAA’s

determination of the cost to the public.

After careful review of all available

information related to the subject

presented above, 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

or add any additional burden upon the

public than was already proposed.

The unsafe condition referenced in

this AD is caused by both stress loads

and corrosion. Stress loads are a direct

result of glider usage. Corrosion can

then develop regardless of whether the

glider is utilized in flight or is on the

ground. With this in mind, the FAA has

determined that the compliance time of

this AD should be in both calendar time

and hours time-in-service (TIS).

The FAA estimates that 30 gliders in

the U.S. registry will be affected by this

proposed AD, that it will take

approximately 8 workhours per glider to

accomplish the required action, and that

the average labor rate is approximately

$60 an hour. Parts will be provided by

the manufacturer at no cost to the

operator. Based on these figures, the

total cost impact of this AD on U.S.

operators is estimated to be $14,400.

This figure is based on the assumption

that no affected glider owner/operator

has accomplished the proposed

replacement of the elevator inner

hinges.

Grob has informed the FAA that

approximately 20 of the affected gliders

already have the required replacement

incorporated. With this in mind, the

cost impact upon the public of the

required action would be reduced from

$14,400 to $5,280.

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
Federal Register / Vol. 60, No. 78 / Monday, April 24, 1995 / Rules and Regulations 20017

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 copy of the final

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, 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:

95–08–13 B. Grob Flugzeugbau:

Amendment 39–9202; Docket No. 94–

CE–30–AD.

Applicability: Model G109B gliders, serial

numbers 6200 through 6445, certificated in

any category.

Note 1: This AD applies to each glider

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

gliders that have been modified, altered, or

repaired so that the performance of the

requirements of this AD is affected, the

owner/operator must use the authority

provided in paragraph (c) of this AD to

request approval from the FAA. This

approval may address either no action, if the

current configuration eliminates the unsafe

condition, or different actions necessary to

address the unsafe condition described in

this AD. Such a request should include an

assessment of the effect of the changed

configuration on the unsafe condition

addressed by this AD. In no case does the

presence of any modification, alteration, or

repair remove any glider from the

applicability of this AD.

Compliance: Required within the next 25

hours time-in-service after the effective date

of this AD or within the next 6 calendar

months after the effective date of this AD,

whichever occurs first, unless already

accomplished.

To prevent failure of the elevator inner

hinges because of delamination or corrosion,

which, if not detected and corrected, could

lead to loss of control of the glider,

accomplish the following:

(a) Replace the elevator inner hinges (2)

with hinges of improved design, part number

109B–3550, in accordance with Grob Repair

Instructions No. 817–25 for Service Bulletin

TM 817–25, dated November 9, 1987.

Note 2: The service instructions of this AD

call for ‘‘the execution of the instructions to

be certified in the log-book by an authorized

inspector class 3.’’ This type of inspector is

not applicable in the United States and the

person accomplishing the AD is as outlined

in part 43 of the Federal Aviation Regulations

(14 CFR part 43). This is not a change over

normal AD procedures.

(b) Special flight permits may be issued in

accordance with §§ 21.197 and 21.199 of the

Federal Aviation Regulations (14 CFR 21.197

and 21.199) to operate gliders 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, Small Airplane

Directorate, FAA, 1201 Walnut, suite 900,

Kansas City, Missouri 64106. The request

should be forwarded through an appropriate

FAA Maintenance Inspector, who may add

comments and then send it to the Manager,

Small Airplane Directorate.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Small Airplane

Directorate.

(d) The replacement required by this AD

shall be done in accordance with Grob Repair

Instructions No. 817–25 for Service Bulletin

TM 817–25, dated November 9, 1987. 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 B. Grob

Flugzeugbau, D–8939 Mattsies, Germany.

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 (39–9202) becomes

effective on June 2, 1995.

Issued in Kansas City, Missouri, on April

11, 1995.

Dwight A. Young,

Acting Manager, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 95–9342 Filed 4–21–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 94–ANE–58; Amendment 39–

9203; AD 95–08–14]

Airworthiness Directives; AlliedSignal,

Inc. (Formerly Textron Lycoming)

LTS101 Series Turboshaft Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that is

applicable to AlliedSignal, Inc.

(formerly Textron Lycoming) LTS101

series turboshaft engines. This action

requires a one-time replacement of

magnetic speed pickups in the engine

electronic overspeed protection system,

or inspection, and replacement, if

necessary, of pickups with incorrect

polarity. This amendment is prompted

by reports of a manufacturing error that

resulted in improper sensor polarity of

magnetic speed pickups. The actions

specified in this AD are intended to

prevent the engine electronic overspeed

protection system from failing to

function as designed, which can result

in the inability to arrest an uncontrolled

power turbine (PT) rotor overspeed and

damage to the aircraft.

DATES: Effective May 9, 1995.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of May 9,

1995.

Comments for inclusion in the Rules

Docket must be received on or before

June 23, 1995.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), New England

Region, Office of the Assistant Chief

Counsel, Attention: Rules Docket No.

94–ANE–58, 12 New England Executive

Park, Burlington, MA 01803–5299.

The service information referenced in

this AD may be obtained from

AlliedSignal Engines, 550 Main Street,

Stratford, CT 06497; telephone (203)

385–1470, fax (203) 385–2256. This

information may be examined 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.

FOR FURTHER INFORMATION CONTACT:

Eugene Triozzi, Aerospace Engineer,

Engine Certification Office, FAA, Engine

and Propeller Directorate, 12 New

England Executive Park, Burlington, MA

01803–5299; telephone (617) 238–7148,

fax (617) 238–7199.