Federal Register / Vol. 62, No. 19 / Wednesday, January 29, 1997 / Proposed Rules 4203

intention to attend the workshop, or if

you wish to be added to the DOE

mailing list for receipt of future rules

and information concerning water

heater matters relating to energy

efficiency.

Issued in Washington, DC on January 22,

1997.

Christine A. Ervin,

Assistant Secretary, Energy Efficiency and

Renewable Energy.

[FR Doc. 97–2173 Filed 1–28–97; 8:45 am]

BILLING CODE 6450–01–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96–CE–65–AD]

RIN 2120–AA64

Airworthiness Directives; Fairchild

Aircraft, Inc. SA226 and SA227 Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes to

supersede AD 96–21–05, which

currently requires the following on

certain Fairchild Aircraft, Inc.

(Fairchild) SA226 and SA227 series

airplanes that do not have a certain

elevator torque tube installed: drilling

inspection access holes in the elevator

torque tube arm, inspecting the elevator

torque tube for corrosion, replacing any

corroded elevator torque tube, and

applying a corrosion preventive

compound. AD 96–21–05 resulted from

several reports of corrosion found in the

elevator torque tube area on the affected

airplanes. The proposed AD would

retain the actions required by AD 96–

21–05, and would add certain Fairchild

Model SA227–BC airplanes to the

Applicability section of that AD. The

actions specified by the proposed AD

are intended to prevent failure of the

flight control system caused by a

corroded elevator torque tube, which

could result in loss of control of the

airplane.

DATES: Comments must be received on

or before April 1, 1997.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Central Region,

Office of the Assistant Chief Counsel,

Attention: Rules Docket No. 96–CE–65–

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

Kansas City, Missouri 64106. Comments

may be inspected at this location

between 8 a.m. and 4 p.m., Monday

through Friday, holidays excepted. Service information that applies to the

proposed AD may be obtained from

Fairchild Aircraft, Inc., P.O. Box

790490, San Antonio, Texas 78279–

0490; telephone (210) 824–9421. This

information also may be examined at

the Rules Docket at the address above.

FOR FURTHER INFORMATION CONTACT: Mr.

Hung Viet Nguyen, Aerospace Engineer,

FAA, Airplane Certification Office, 2601

Meacham Boulevard, Fort Worth, Texas

76193–0150; telephone (817) 222–5155;

facsimile (817) 222–5960.

SUPPLEMENTARY INFORMATION:

Comments Invited

Interested persons are invited to

participate in the making of the

proposed rule by submitting such

written data, views, or arguments as

they may desire. Communications

should identify the Rules Docket

number and be submitted in triplicate to

the address specified above. All

communications received on or before

the closing date for comments, specified

above, will be considered before taking

action on the proposed rule. The

proposals contained in this notice may

be changed in light of the comments

received.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the proposed 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

proposal will be filed in the Rules

Docket.

Commenters wishing the FAA to

acknowledge receipt of their comments

submitted in response to this notice

must submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket No. 96–CE–65–AD.’’ The

postcard will be date stamped and

returned to the commenter.

Availability of NPRMs

Any person may obtain a copy of this

NPRM by submitting a request to the

FAA, Central Region, Office of the

Assistant Chief Counsel, Attention:

Rules Docket No. 96–CE–65–AD, Room

1558, 601 E. 12th Street, Kansas City,

Missouri 64106.

Events Leading to the Proposed AD

AD 96–21–05, Amendment 39–9782

(61 FR 54538, October 21, 1996),

currently requires the following on

certain Fairchild Aircraft SA226 and

SA227 series airplanes that do not have

a part number (P/N) 27–44026–007

elevator torque tube installed:

• Drilling inspection access holes in

the elevator torque tube arm;

• Inspecting the elevator torque tube

for corrosion and replacing any

corroded elevator torque tube; and

• Applying a corrosion preventive

compound.

Accomplishment of the inspection

access hole drilling, the inspection, and

the corrosion preventive compound

application is in accordance with either

Fairchild Aircraft Service Bulletin (SB)

226–27–050 or Fairchild Aircraft SB

227–27–028, both issued: January 22,

1990.

AD 96–21–05 resulted from several

reports of corrosion found in the

elevator torque tube area on the affected

airplanes.

The FAA has since determined that

the requirements of AD 96–21–05

should also apply to certain Fairchild

Model SA227–BC airplanes. In addition,

Fairchild has issued an engineering

order that provides instructions for

reworking the elevator torque tube.

When reworked, the elevator torque

tube is identified as P/N 27–44026–

SEO–1–03.

The FAA has also determined that

airplane owners/operators should not

have to accomplish the actions of AD

96–21–05 if the affected airplane

incorporates an elevator torque tube

with either P/N 27–44026–005, P/N 27–

44026–007, or P/N 27–44026–SEO–1–

03.

The FAA’s Determination

After examining the circumstances

and reviewing all available information

related to the incidents described above,

the FAA has determined that AD action

should be taken to prevent failure of the

flight control system caused by a

corroded elevator torque tube, which

could result in loss of control of the

airplane.

Explanation of the Provisions of the

Proposed AD

Since an unsafe condition has been

identified that is likely to exist or

develop in other Fairchild SA226 and

SA227 series airplanes of the same type

design, the FAA is proposing an AD that

would supersede AD 96–21–05. The

proposed AD would (1) retain the

requirements of drilling inspection

access holes in the elevator torque tube

arm, inspecting the elevator torque tube

for corrosion and replacing any

corroded elevator torque tube, and

applying a corrosion preventive

compound; (2) add certain Fairchild
4204 Federal Register / Vol. 62, No. 19 / Wednesday, January 29, 1997 / Proposed Rules

Model SA227–BC airplanes to the

Applicability section of the AD; and (3)

exempt from the AD those airplanes

incorporating an elevator torque tube

with either P/N 27–44026–005, P/N 27–

44026–007, or P/N 27–44026–SEO–1–

03. Accomplishment of the proposed

inspection access hole drilling, the

inspection, and the corrosion preventive

compound application would still be in

accordance with either Fairchild

Aircraft SB 226–27–050 or Fairchild

Aircraft SB 227–27–028, both Issued:

January 22, 1990.

Compliance Time of the Proposed AD

The compliance time for the proposed

AD is presented in calendar time

instead of hours time-in-service (TIS).

The FAA has determined that a calendar

time for compliance would be the most

desirable method because the unsafe

condition described by the proposed AD

is caused by corrosion. Corrosion can

occur on airplanes regardless of whether

the airplane is in service or on the

ground.

Cost Impact

The FAA estimates that 396 airplanes

in the U.S. registry would be affected by

the proposed AD, that it would take

approximately 10 workhours per

airplane to accomplish the proposed

action, and that the average labor rate is

approximately $60 an hour. Based on

these figures, the total cost impact of the

proposed AD on U.S. operators is

estimated to be $237,600. This figure is

based on the presumption that no

owner/operator of the affected airplanes

has accomplished the proposed

inspection access hole drilling,

inspection, or corrosion preventive

compound application. It also is based

on the presumption that no elevator

torque tube would be found corroded

and need to be replaced.

AD 96–21–05 currently requires the

same actions as is proposed for 390 of

the affected airplanes. The actions

specified in this proposed AD would

affect only six additional airplanes over

that already required by AD 96–21–05.

With this in mind, the cost impact of the

proposed AD over that already required

by AD 96–21–05 would be $3,600.

Regulatory Impact

The regulations proposed herein

would 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

proposal would 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) if

promulgated, 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 draft

regulatory evaluation prepared for this

action has been placed 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, Safety.

The Proposed Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration proposes to amend 14

CFR part 39 of the Federal Aviation

Regulations 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 Airworthiness Directive (AD)

96–21–05, Amendment 39–9782, and by

adding a new AD to read as follows:

Fairchild Aircraft, Inc.: Docket No. 96–CE–

65–AD; Supersedes AD 96–21–05,

Amendment 39–9782.

Applicability: The following airplane

models and serial numbers, certificated in

any category, that do not incorporate an

elevator torque tube with either part number

(P/N) 27–44026–005, P/N 27–44026–007, or

P/N 27–44026–SEO–1–03:

Model Serial Nos.

SA226–T .. T201 through T275 and T277

through T291.

SA226–

T(B).

T(B)276 and T(B)292 through

T(B)417.

SA226–AT AT001 through AT074.

SA226–TC TC201 through TC419.

SA227–TT TT421 through TT541.

SA227–AT AT423 through AT695.

SA227–AC AC406, AC415, AC416, and

AC420 through AC772.

SA227–BC BC762, BC764, BC766, BC770,

BC771, and BC772.

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 within the next six

calendar months after the effective date of

this AD, unless already accomplished

(compliance with AD 96–21–05).

To prevent failure of the flight control

system caused by a corroded elevator torque

tube, which could result in loss of control of

the airplane, accomplish the following:

(a) Drill two .5-inch diameter holes in the

inboard side of the elevator torque tube arm

in accordance with the ACCOMPLISHMENT

INSTRUCTIONS section of, and as specified

in Figure 1 of, Fairchild Aircraft Service

Bulletin (SB) 226–27–050 or Fairchild

Aircraft SB 227–27–028, both Issued: January

22, 1990, as applicable.

(b) Inspect the elevator torque tube in

accordance with the ACCOMPLISHMENT

INSTRUCTIONS section of Fairchild Aircraft

SB 226–27–050 or Fairchild Aircraft SB 227–

27–028, both Issued: January 22, 1990, as

applicable.

(1) If corrosion is found inside the elevator

torque tube, prior to further flight after the

inspection required by paragraph (b) of this

AD, replace the corroded elevator torque tube

with either a P/N 27–44026–005, P/N 27–

44026–007, or P/N 27–44026–SEO–1–03

elevator torque tube in accordance with the

applicable maintenance manual.

(2) If corrosion is not found inside the

elevator torque tube, prior to further flight

after the inspection required by paragraph (b)

of this AD, apply a corrosion preventive

compound in accordance with the

ACCOMPLISHMENT INSTRUCTIONS

section of Fairchild Aircraft SB 226–27–050

or Fairchild Aircraft SB 227–27–028, both

Issued: January 22, 1990, as applicable.

(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) An alternative method of compliance or

adjustment of the compliance time that

provides an equivalent level of safety may be

approved by the Manager, Airplane

Certification Office (ACO), FAA, 2601

Meacham Boulevard, Fort Worth, Texas

76193–0150. The request shall be forwarded

through an appropriate FAA Maintenance

Inspector, who may add comments and then

send it to the Manager, Fort Worth ACO.

Alternative methods of compliance approved

in accordance with AD 96–21–05

(superseded by this AD) are considered

approved for this AD.

Note 2: Information concerning the

existence of approved alternative methods of
Federal Register / Vol. 62, No. 19 / Wednesday, January 29, 1997 / Proposed Rules 4205

compliance with this AD, if any, may be

obtained from the Fort Worth ACO.

(e) All persons affected by this directive

may obtain copies of the service bulletins

referred to herein upon request to Fairchild

Aircraft, P.O. Box 790490, San Antonio,

Texas 78279–0490; or may examine these

service bulletins at the FAA, Central Region,

Office of the Assistant Chief Counsel, Room

1558, 601 E. 12th Street, Kansas City,

Missouri 64106.

(f) This amendment supersedes AD 96–21–

05, Amendment 39–9782.

Issued in Kansas City, Missouri, on January

21, 1997.

Henry A. Armstrong,

Acting Manager, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 97–2103 Filed 1–28–97; 8:45 am]

BILLING CODE 4910–13–P

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96–CE–37–AD]

RIN 2120–AA64

Airworthiness Directives; Burkhart

Grob, Luft- und Raumfahrt, Model G

103 C Twin III SL Sailplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes to

adopt a new airworthiness directive

(AD) that would apply to the Burkhart

Grob, Luft- und Raumfahrt (Grob) Model

G 103 C Twin III SL sailplanes. The

proposed action would require

inspecting the propeller bearing and

upper pulley wheel for increased play

and, if increased play is found,

modifying the propeller bearing and

pulley wheel with a part of improved

design. The proposed action is

prompted by two reports of Model G

103 C Twin III SL sailplanes losing the

engine propeller while in flight and one

operator finding increased play in the

sailplane propeller during an

inspection. The actions specified by the

proposed AD are intended to prevent

the loss of the sailplane engine propeller

and possibly causing loss of the

sailplane.

DATES: Comments must be received on

or before April 3, 1997.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Central Region,

Office of the Assistant Chief Counsel,

Attention: Rules Docket No. 96–CE–37–

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

Kansas City, Missouri 64106. Comments

may be inspected at this location

between 8 a.m. and 4 p.m., Monday

through Friday, holidays excepted.

Service information that applies to the

proposed AD may be obtained from

Burkhart Grob Luft und Raumfahrt, D–

86874 Mattsies, Germany. This

information also may be examined at

the Rules Docket at the address above.

FOR FURTHER INFORMATION CONTACT: Mr.

J. Mike Kiesov, Project Officer,

Sailplanes, Small Airplane Directorate,

Airplane Certification Service, FAA,

1201 Walnut, suite 900, Kansas City,

Missouri, 64106; telephone (816) 426–

6934, facsimile (816) 426–2169.

SUPPLEMENTARY INFORMATION:

Comments Invited

Interested persons are invited to

participate in the making of the

proposed rule by submitting such

written data, views, or arguments as

they may desire. Communications

should identify the Rules Docket

number and be submitted in triplicate to

the address specified above. All

communications received on or before

the closing date for comments, specified

above, will be considered before taking

action on the proposed rule. The

proposals contained in this notice may

be changed in light of the comments

received.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the proposed 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

proposal will be filed in the Rules

Docket.

Commenters wishing the FAA to

acknowledge receipt of their comments

submitted in response to this notice

must submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket No. 96–CE–37–AD.’’ The

postcard will be date stamped and

returned to the commenter.

Availability of NPRMs

Any person may obtain a copy of this

NPRM by submitting a request to the

FAA, Central Region, Office of the

Assistant Chief Counsel, Attention:

Rules Docket No. 96–CE–37–AD, Room

1558, 601 E. 12th Street, Kansas City,

Missouri 64106.

Events Leading to the Proposed Action

The Luftfahrt-Bundesamt (LBA),

which is the airworthiness authority for

Germany, recently notified the FAA that

an unsafe condition may exist on certain

Grob Model G 103 C Twin III SL

sailplanes, serial numbers (S/N) 35002

through 35051. The LBA reports that

two Model G 103 C Twin III SL

sailplanes lost the engine propeller

while in flight, and one operator found

increased play in the sailplane propeller

bearing and upper pulley wheel during

an inspection. Increased play is defined

by measuring the movement at the outer

edge of the brake disc. If the movement

exceeds or is equal to 0.4 mm, then the

outer bearing and upper pulley wheel

would need to be replaced. This

increased play could start rotating the

outer bearing races and damage the

grooved nut, subsequently causing the

engine propeller to come loose and

possibly fall off. This condition, if not

detected and corrected, could result in

loss of the sailplane.

Grob has issued Service Bulletin (SB)

869–18, dated March 7, 1996, and SB

869–18/2, dated July 8, 1996, that

revises page six of SB 869–18, which

specifies inspecting the propeller

bearing for increased play and

modifying the propeller bearing, if

increased play is found.

FAA’s Determination

This sailplane model is manufactured

in Germany and is type certificated for

operation in the United States under the

provisions of section 21.29 of the

Federal Aviation Regulations (14 CFR

21.29) and the applicable bilateral

airworthiness agreement. Pursuant to

this bilateral airworthiness agreement,

the LBA has kept the FAA informed of

the situation described above. The FAA

has examined the findings of the LBA,

reviewed all available information, and

determined that AD action is necessary

for products of this type design that are

certificated for operation in the United

States.

Explanation of the Provisions of the

Proposed AD

Since an unsafe condition has been

identified that is likely to exist or

develop in other Grob G 103 C Twin III

SL sailplanes of the same type design,

the proposed AD would require

repetitively inspecting the propeller

bearing and pulley wheel for increased

play, eventually modifying the propeller

bearing and upper pulley wheel by

installing a part of improved design.

Related Service Information

Accomplishment of the proposed

action would be in accordance with

Grob Service Bulletin (SB) 869–18,

dated March 7, 1996, and Grob SB 869–

18/2, dated July 8, 1996, which is a