27926 Federal Register / Vol. 60, No. 102 / Friday, May 26, 1995 / Proposed Rules

proposal, and should address the

following concerns: (1) The interaction

between SBA programs and the

procurement process, including the

various statutory authorities impacting

this process; (2) the effect on small

business participation; and (3) the

prospects for significant new entrants

into the Federal procurement market.

Compliance With Executive Orders

12866, 12778 and 12612, the Regulatory

Flexibility Act (5 U.S.C. 601, et seq.),

and the Paperwork Reduction Act (44

U.S.C. Chap. 35)

The SBA believes that this proposed

rule, if finalized, would have a

significant impact on a substantial

number of small entities within the

meaning of the Regulatory Flexibility

Act, 5 U.S.C. 601, et seq. In addition,

this rule constitutes a significant rule for

the purpose of Executive Order 12866.

A regulatory flexibility analysis follows:

(1) Description of Entities to Which This

Rule Applies

With eleven million small purchase

contract actions during FY 1993, the

SBA estimates that tens of thousands of

small manufacturers active in Federal

contracting potentially could be

impacted by this rule. In addition,

thousands of non-manufacturers or

dealers providing manufactured

products under small purchase

procedures could be impacted by this

rule since their product mix and small

business status could be affected.

(2) Description of Potential Benefits of

This Rule

A decision to apply the nonmanufacturer rule to supply contracts in

the $2,500 to $25,000 range of contract

size would have an estimated impact on

small business participation in excess of

$100 million. During FY 1993, $7.9

billion was awarded to small business

concerns under small purchase

procedures. Although available data

would not permit the SBA to determine

the extent to which Federal agencies

utilize small business nonmanufacturers to satisfy contracts

awarded as small purchases, or to

identify which contracts are in the

$2,500 to $25,000 range affected by this

rule, the magnitude of the $7.9 billion

figure suggests that a decision to apply

the non-manufacturer rule waiver to

small business procurements in this

dollar range would likely have an

annual small business impact exceeding

$100 million.

(3) Description of the Potential Costs of

This Rule

The SBA believes the procurement

costs to the Federal government would

be minimal. All set-aside and 8(a)

contracts are expected to be awarded at

no more than fair-market value. If

reasonable pricing does not exist, the

procuring agency should issue an

unrestricted solicitation. There should

be no significant increased costs to the

government.

(4) Description of the Potential Net

Benefits of the Rule

If the proposed rule is adopted, the

SBA estimates that tens of thousands of

small manufacturers would provide the

products that formerly have been

provided by large manufacturers. At a

minimal cost to the government, small

business participation in the Federal

market would likely be increased. The

direct impact would be entirely

concentrated in the area of Federal

procurement.

(5) Legal Basis for This Rule

The legal basis for this rule is sections

3(a), 5(a), 8(a), and 15(a) of the Small

Business Act, 15 U.S.C. 632(a),

634(b)(6), 637(a) and 644(a).

(6) Federal Rules

There are no Federal rules which

duplicate, overlap or conflict with this

proposed rule. The SBA has been given

exclusive statutory jurisdiction in

establishing size standards.

(7) Significant Alternatives to This Rule

In compliance with the Regulatory

Flexibility Act, the SBA has examined

alternatives to the proposed application

of the non-manufacturer rule. These are

discussed in the supplementary

information. The public is invited to

comment on the proposed rule and

alternative approaches to assist the SBA

in developing a final rule.

For purpose of the Paperwork

Reduction Act, 44 U.S.C. Ch. 35, SBA

certifies that this rule contains no new

reporting or recordkeeping

requirements.

For purposes of Executive Order

12612, SBA certifies that this rule does

not have any federalism implications

warranting the preparation of a

Federalism Assessment.

For the reasons set forth above, Title

13, Code of Federal Regulations (CFR),

is amended as set forth below.

PART 121—[AMENDED]

1. The authority citation for 13 CFR

Part 121 continues to read as follows:

Authority: 15 U.S.C. 632(a), 634(b)(6),

637(a), 644(c); and Pub. L. 102–486, 106 Stat.

2776, 3133.

§ 121.906 [Amended]

2. Section 121.906(d) is removed.

Dated: April 19, 1995.

Philip Lader,

Administrator.

[FR Doc. 95–12646 Filed 5–25–95; 8:45 am]

BILLING CODE 8025–01-M

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 95–SW–06–AD]

Airworthiness Directives; Robinson

Helicopter Company Model R22 Series

Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes the

supersedure of an existing airworthiness

directive (AD), applicable to Robinson

Helicopter Company Model R22 series

helicopters, that currently requires an

inspection and repetitive visual checks

for slippage of the tail rotor (T/R) drive

and replacement of the T/R gearbox, if

necessary. This action would require

disassembly of the T/R gearbox to verify

the installation of the input and output

shaft keys (keys) between the input and

output pinions and their respective

shafts. This proposal is prompted by

two incidents in which the key was not

installed between the output shaft and

the output pinion during assembly of

the T/R gearbox at Robinson Helicopter

Company. The actions specified by the

proposed AD are intended to prevent

slippage of the T/R drive, loss of

directional control, and subsequent loss

of control of the helicopter.

DATES: Comments must be received by

July 25, 1995.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Office of the

Assistant Chief Counsel, Attention:

Rules Docket No. 95–SW–06–AD, 2601

Meacham Blvd., Room 663, Fort Worth,

Texas 76137. Comments may be

inspected at this location between 9:00

a.m. and 3:00 p.m., Monday through

Friday, except Federal holidays.

FOR FURTHER INFORMATION CONTACT: Ms.

Elizabeth Bumann, Aerospace Engineer,

FAA, Los Angeles Aircraft Certification

Office, 3960 Paramount Blvd.,
Federal Register / Vol. 60, No. 102 / Friday, May 26, 1995 / Proposed Rules 27927

Lakewood, California 90712, telephone

(310) 627–5265, fax (310) 627–5210.

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

summarizing 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. 95–SW–06–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, Office of the Assistant Chief

Counsel, Attention: Rules Docket No.

95–SW–06–AD, 2601 Meacham Blvd.,

Room 663, Fort Worth, Texas 76137.

Discussion

On August 25, 1994, the FAA issued

priority letter AD 94–17–07, applicable

to Robinson Helicopter Company Model

R22 series helicopters, to require an

inspection and repetitive visual checks

for slippage of the T/R drive and

replacement of the T/R gearbox, if

necessary. On October 24, 1994, the

FAA issued the final rule of the priority

letter, AD 94–17–07, Amendment 39–

9059 (59 FR 55203, November 4, 1994).

Those actions were prompted by two

incidents in which the key was not

installed between the output shaft and

the output pinion during assembly of

the T/R gearbox. The key is required to

prevent the output gear from rotating on

the output shaft. Both incidents resulted

in slippage of the T/R drive. The

requirements of that AD are intended to

prevent slippage of the T/R drive, loss

of directional control, and subsequent

loss of control of the helicopter. Owner/

operator daily preflight checks for

misalignment of the alignment dots that

are installed on the tail cone skin and

the drive shaft flange are allowed. These

owner/operator checks do not require

the use of tools, precision measuring

equipment, training, pilot logbook

endorsements, or the use of technical

data not contained in the AD.

Additionally, these owner/operator

checks are considered part of the normal

pilot ‘‘Before Takeoff’’ and ‘‘After

Landing’’ checks. These owner/operator

checks are additional measures to

prevent slippage of the T/R drive until

the installation of the keys is verified.

These checks may be performed by an

owner/operator holding at least a

private pilot certificate, but must be

entered into the aircraft records showing

compliance with this AD in accordance

with sections 43.11 and 91.417 (a)(2)(v)

of the Federal Aviation Regulations.

Since the issuance of that AD, the

FAA has determined that the required

terminating action to AD 94–17–07 is

verification of the presence of both keys

through disassembly and reassembly of

the T/R gearbox in accordance with the

procedures contained in this notice, or

other FAA-approved procedures.

Since an unsafe condition has been

identified that is likely to exist or

develop on other Robinson Helicopter

Company Model R22 series helicopters

of the same type design, the proposed

AD would supersede AD 94–17–07 to

require disassembly of the T/R gearbox

to verify the installation of the key

between the input and output pinions

and their respective shafts.

The FAA estimates that 500

helicopters of U.S. registry would be

affected by this proposed AD, that it

would take approximately 5 work hours

per helicopter to accomplish the

proposed actions, and that the average

labor rate is $60 per work hour. Based

on these figures, the total cost impact of

the proposed AD on U.S. operators is

estimated to be $150,000.

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 proposed regulation (1)

Is not a ‘‘significant regulatory action’’

under Executive Order 12866; (2) is not

a ‘‘significant rule’’ under the 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 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, Safety.

The Proposed Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration proposes to amend 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 39–9059 (59 FR

55203, November 4, 1994), and by

adding a new airworthiness directive

(AD), to read as follows:

Robinson Helicopter Company: Docket No.

95–SW–06–AD. Supersedes AD 94–17–

07, Amendment 39–9059.

Applicability: Model R22 series

helicopters, certificated in any category with

tail rotor (T/R) gearboxes that were

manufactured or overhauled by Robinson

Helicopter Company prior to June 8, 1992.

The following gearbox serial numbers have

been determined to have the T/R input and

output shaft keys installed and are therefore

exempt from this AD: 0012, 0013, 0014, 0020,

0021, 0040, 0054, 0062, 0091, 0095, 0098,

0108, 0121, 0134, 0137, 0153, 0169, 0179,

0185, 0191, 0201, 0205, 0227, 0228, 0235,

0248, 0258, 0262, 0272, 0277, 0280, 0321,

0333, 0342, 0365, 0432, 0439, 0444, 0503,

0504, 0525, 0548, 0558, 0559, 0565, 0574,

0576, 0592, 0594, 0597, 0603, 0604, 0605,

0615, 0632, 0641, 0644, 0650, 0656, 0662,

0663, 0674, 0686, 0689, 0696, 0697, 0700,

0702, 0707, 0722, 0734, 0735, 0736, 0742,

0759, 0767, 0777, 0778, 0805, 0832, 0836,

0839, 0842, 0850, 0862, 0866, 0868, 0887,

0892, 0937, 0939, 0983, 0986, 0996, 0998,
27928 Federal Register / Vol. 60, No. 102 / Friday, May 26, 1995 / Proposed Rules

1018, 1021, 1029, 1030, 1035, 1072, 1081,

1087, 1104, 1116, 1121, 1126, 1129, 1132,

1141, 1151, 1176, 1186, 1187, 1199, 1205,

1208, 1217, 1222, 1228, 1233, 1245, 1249,

1269, 1274, 1290, 1293, 1299, 1301, 1307,

1311, 1323, 1330, 1333, 1339, 1341, 1350,

1361, 1379, 1385, 1388, 1392, 1404, 1412,

1428, 1438, 1442, 1450, 1460, 1468, 1494,

1499, 1505, 1509, 1512, 1514, 1526, 1541,

1544, 1578, 1586, 1593, 1595, 1597, 1605,

1610, 1627, 1628, 1636, 1643, 1647, 1648,

1652, 1654, 1686, 1687, 1698, 1701, 1702,

1706, 1710, 1724, 1731, 1732, 1738, 1741,

1750, 1752, 1757, 1759, 1769, 1783, 1800,

1803, 1808, 1814, 1816, 1830, 1844, 1846,

1851, 1852, 1861, 1868, 1871, 1886, 1889,

1901, 1911, 1912, 1927, 1928, 1948, 1959,

1961, 1963, 1965, 1992, 2025, 2034, 2037,

2051, 2071, 2100, 2101, 2103, 2126, 2129,

2136, 2160, 2166, 2170, 2180, 2193, 2203,

2242, 2254, 2265, 2269, 2272, 2279, 2280,

2283, 2294, 2298, 2299, 2304, 2314, 2357,

2377, 2380, 2381, 2395, 2406, 2420, 2421,

2422, 2423, 2425, 2431, 2435, 2436, 2459,

2479, 2492, 2498, 2531, 2539, 2574, 2579,

2582, 2587, 2627, 2634, 2672, 2683, 2697,

2716, 2719, 2721, 2731, 2797, 2863, 2937,

2945.

Note 1: This AD applies to each helicopter

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

helicopters 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 (d) 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 helicopter

from the applicability of this AD.

Compliance: Required as indicated, unless

accomplished previously.

To prevent slippage of the T/R drive, loss

of directional control, and subsequent loss of

control of the helicopter, accomplish the

following:

(a) Before further flight, install alignment

dots as follows:

(1) Remove the transparent inspection

cover on the tail cone and rotate the T/R

blades so that one blade leading edge is

aligned with the tail cone centerline. Mark a

dot on the tail cone skin aligned with the tip

of the blade leading edge. With the same

alignment, mark a dot on the centerline of the

tail cone skin at the edge of the inspection

hole, and mark a corresponding dot on the

drive shaft flange.

(2) Position the aft T/R blade with leading

edge approximately 45-degrees above

horizontal. Engage the clutch and rotor brake

if the helicopter is so equipped. Use the

engine ring gear holding tool, part number

(P/N) MT091–1, or an FAA-approved

equivalent, to keep the engine from rotating.

(b) Conduct the following daily preflight

checks for misalignment of the alignment

dots until compliance with paragraph (c) of

this AD has been accomplished: Check for

misalignment of the alignment dots installed

on the tail cone skin and the drive shaft

flange by rotating the T/R blade so that the

alignment dot is visible in the inspection

window and the tip of the T/R blade leading

edge aligns with the dot on the tail cone skin.

Ensure that the drive shaft flange dot is

aligned with the dot on the centerline of the

tail cone skin at the edge of the inspection

window. If any misalignment is detected,

before further flight, replace the T/R gearbox

with an airworthy one that has been

determined to have both the input and

output keys installed in accordance with

paragraph (c) of this AD or other FAAapproved procedures, or is exempt from the

requirements of this AD as listed in the

applicability section of this AD. The checks

required by this AD may be performed by an

owner/operator holding at least a private

pilot certificate and must be entered into the

aircraft records showing compliance with

this AD, in accordance with sections 43.11

and 91.417(a)(2)(v) of the Federal Aviation

Regulations.

(c) Within the next 100 hours time-inservice (TIS) after the effective date of this

AD, or at the next annual inspection,

whichever occurs first, verify installation of

both the input and output shaft keys as

follows:

(1) Cut and remove the safety wire securing

the chip detector to the sight gage on the T/

R gearbox. Place a container under the T/R

gearbox to catch the drained oil and remove

the chip detector. Remove and discard the

gasket on the chip detector.

(2) Remove the T/R gearbox from the

helicopter in accordance with the applicable

maintenance manual.

(3) Cut and remove the safety wire securing

the filler vent plug to the sight gage on the

T/R gearbox and remove the filler vent plug

and sight gage. Remove and discard the

gasket on the filler vent plug and sight gage.

(4) Remove and disassemble the output

cartridge, P/N A111–1, from the T/R gearbox

case, P/N A109–1 (see figure 1) as follows:

(i) Place a mark across the gear case, P/N

A109–1, and output cartridge, P/N A111–1,

with a felt pen or grease pencil to ensure

proper reassembly.

(ii) Cut and remove the safety wire around

the four MS20074–04–06 bolts, securing the

output cartridge to the gear case. Remove the

four bolts and AN960–416L washer(s).

Separate the output cartridge from the gear

case (see figure 1).

(iii) Remove and discard the safety wire,

MS16562–24 or 52–022–094–0437 roll pin,

and MS14145L6 or LCN6M–624 retaining

nut. Remove the AN960–616L washer(s) and

the washer, P/N A141–2, noting the

washer(s) location for reassembly. Do not

damage the output shaft, P/N A107–1, or the

shim(s), P/N A118–1 through -6, located next

to the flange of the output cartridge when

removing the retaining nut.

(iv) Visually inspect for the presence of the

output shaft key, P/N A114–2, between the

pinion gear, P/N A545–1, and the output

shaft (see figure 2).

(v) If the output shaft key is missing,

replace the T/R gearbox with an airworthy

one that has been determined to have the

output key installed. Report any T/R gearbox

that has a missing key within 10 days after

the inspection to the Manager, Los Angeles

Manufacturing Inspection Office, FAA,

Northwest Mountain Region, 3960

Paramount Blvd., Lakewood, California

90712, telephone (310) 627–5290, fax (310)

627–5293. Reporting requirements have been

approved by the Office of Management and

Budget and assigned OMB control number

2120–0056.

(vi) If the output key is installed, reinstall

the washer, P/N A141–2, and AN960–616L

washer(s). Install a MS14145L6 or LCN6M–

624 retaining nut, and torque to 200–250 in.-

lbs. plus 20–25 in.-lbs. nut drag (maximum

275 in.-lbs.). Install a MS16562–24 or 52–

022–094–0437 roll pin, and safety wire using

0.032-inch stainless steel safety wire. The

safety wire pigtail must be wrapped tightly

around the retaining nut. Vibro-etch the final

rule AD number on the output cartridge

attachment flange.

(5) Remove and disassemble the input

cartridge, P/N A110–1, from the T/R gear

case, P/N A109–1, as follows:

(i) Place two marks across the gear case, P/

N A109–1, and input cartridge, P/N A110–1,

with a felt pen or grease pencil to ensure

proper reassembly.

(ii) Cut and remove the safety wire around

the four MS20074–04–06 bolts securing the

input cartridge to the gear case. Remove the

four bolts and AN960–416L washer(s).

Separate the input cartridge from the gear

case (see figure 1).

(iii) Secure the input cartridge to a block

of wood through the two bolt holes in the

input shaft assembly, P/N A116–1 (see figure

1). Place the block of wood in a vise. Remove

and discard the safety wire, roll pin, and

retaining nut. Remove the AN960–616L

washer(s), and washer, P/N A141–1, noting

the washer(s) location for reassembly. Do not

damage the input shaft or shim(s), P/N A118–

1 through –6, located next to the flange of the

input cartridge.

(iv) Visually inspect for the presence of the

input shaft key, P/N A114–1, between the

gear, P/N A545–2, and the input shaft (see

Note on figure 2).

(v) If the input shaft key is missing, replace

the T/R gearbox with an airworthy one that

has been determined to have the input key

installed. Report any T/R gearbox that has a

missing key within 10 days after the

inspection to the Manager, Los Angeles

Manufacturing Inspection District Office,

FAA, Northwest Mountain Region, 3960

Paramount Blvd., Lakewood, California

90712, telephone (310) 627–5290, fax (310)

627–5293. Reporting requirements have been

approved by the Office of Management and

Budget, and assigned OMB control number

2120–0056.

(vi) If the input key is installed, reinstall

the AN960–616L washer(s) and washer, P/N

A141–1. Install a MS14145L6 or LCN6M–624

retaining nut, and torque to 200–250 in.-lbs.

plus 20–25 in.-lbs. nut drag (maximum 275

in.-lbs.). Install a MS16562–24 or 52–022–

094–0437 roll pin and safety wire using

0.032-inch stainless steel safety wire. The

safety wire pigtail must be wrapped tightly

around the retaining nut. Remove the two
Federal Register / Vol. 60, No. 102 / Friday, May 26, 1995 / Proposed Rules 27929

bolts securing the input shaft assembly to the

block of wood. Vibro-etch the final rule AD

number on the input cartridge attachment

flange.

(6) Reassemble the input and output

cartridges to the T/R case as follows:

(i) Color the ‘‘X’’ marked on the pinion

gear, P/N A545–1, (one tooth only) of the

output cartridge and on the gear, P/N A545–

2, (located on two consecutive teeth) of the

input cartridge with a red marker to make

reinstallation easier. Note that these three

gear teeth may already be colored (see figure

3).

(ii) Visually inspect the edge of the

chamfers in the gear case, making sure they

are round and smooth so that the O-ring will

not be damaged upon installation.

(iii) Remove and discard the O-ring on both

the input cartridge and output cartridge.

Replace the O-ring with National P/N AS142

B46–70, or Parker P/N 2–142 N674–70 Oring. Lubricate the replacement O-ring with

oil, P/N A257–2, and install an O-ring on

each cartridge.

(iv) Reinstall the output cartridge on the

gear case with four MS20074–04–06 bolts

and AN960–416L washers. Reinstall the

input cartridge on the gear case with four

MS20074–04–06 bolts and AN960–416L

washers. Do not torque the bolts.

(v) Look through the sight gage opening

while using a flashlight pointed into the filler

vent hole to verify the gears are meshed

properly. Gears are properly meshed when

the ‘‘X’’ marked on the pinion gear of the

output cartridge is between the two ‘‘X’s’’

marked on the gear of the input cartridge (see

figure 3). Do not torque the bolts until both

cartridges are installed on the case and the

gears are properly meshed. Torque the output

cartridge first, then the input cartridge to 60

in.-lbs. Safety wire with 0.032-inch stainless

steel safety wire.

(vi) Reinstall sight gage with MS35769–11

or AN900–10 gasket. Oil threads to prevent

threads from locking up. Torque to 200 in.-

lbs.

(vii) Reinstall the chip detector with a

MS35769–8 or AN900–9 gasket after

lubricating the threads with oil. Torque the

chip detector to 150 in.-lbs. Safety wire the

sight gage to the chip detector using 0.032-

inch stainless steel safety wire.

(viii) Fill the T/R gearbox with oil to the

level indicated on the T/R sight glass decal.

Reinstall the filler vent plug, P/N A610–1,

with a MS35769–9 or AN900–8 gasket, after

lubricating the threads with oil.

(ix) Inspect the T/R gearbox assembly to

ensure that the shafts and gears rotate freely.

(7) Reinstall the T/R gearbox onto the

helicopter in accordance with the applicable

maintenance manual. Verify that the oil level

of the T/R gearbox is at the recommended

mark on the sight glass.

(d) 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 2: 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.

(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 helicopter

to a location where the requirements of this

AD can be accomplished.

BILLING CODE 4910–13–P
27930 Federal Register / Vol. 60, No. 102 / Friday, May 26, 1995 / Proposed Rules
Federal Register / Vol. 60, No. 102 / Friday, May 26, 1995 / Proposed Rules 27931
27932 Federal Register / Vol. 60, No. 102 / Friday, May 26, 1995 / Proposed Rules

BILLING CODE 4910–13–C Issued in Fort Worth, Texas, on May 19,

1995.

Eric Bries,

Acting Manager, Rotorcraft Directorate,

Aircraft Certificatin Service.

[FR Doc. 95–12955 Filed 5–25–95; 8:45 am]

BILLING CODE 4910–13–P