Federal Register / Vol. 60, No. 239 / Wednesday, December 13, 1995 / Proposed Rules 63991

registry would be affected by this

proposed AD.

The actions that are currently

required by AD 90–20–16 take

approximately 21 work hours per

airplane to accomplish, at an average

labor rate of $60 per work hour.

Required parts cost approximately

$5,500 per airplane. Based on these

figures, the cost impact on U.S.

operators of the actions currently

required is estimated to be $1,304,680,

or $6,760 per airplane.

For certain affected airplanes, the new

replacement (terminating) action that is

proposed in this AD would take

approximately 1 work hour per airplane

to accomplish, at an average labor rate

of $60 per work hour. The cost of

required replacement parts is estimated

to be $5,500 per airplane. Based on

these figures, the cost impact on U.S.

operators of the proposed requirements

of this AD is estimated to be $5,560 per

airplane.

The cost impact figures discussed

above are based on assumptions that no

operator has yet accomplished any of

the current or proposed requirements of

this AD action, and that no operator

would accomplish those actions in the

future if this AD were not adopted.

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 USC 106(g), 40101, 40113,

44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

removing amendment 39–6726 (55 FR

37858, September 14, 1990), and by

adding a new airworthiness directive

(AD), to read as follows:

Boeing: Docket 95–NM–124–AD. Supersedes

AD 90–20–16, Amendment 39–6726.

Applicability: Model 767 series airplanes,

as listed in Boeing Service Bulletin 767–57–

0021, Revision 1, dated September 14, 1989,

or Revision 5, dated June 15, 1995;

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 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 airplane from the

applicability of this AD.

Compliance: Required as indicated, unless

accomplished previously. To prevent loss of

the pilot’s ability to control the affected slat,

which could adversely affect the

controllability of the airplane, accomplish

the following:

(a) For airplanes having line positions 1

through 235 inclusive: Within the next 1,200

landings or 9 months after October 23, 1990

(the effective date of AD 90–20–16,

amendment 39–6726), whichever occurs first,

unless accomplished within the last 800

landings or 6 months, whichever occurs later,

perform a visual inspection to determine the

date of manufacture of the control rods of the

outboard leading edge slat of the wings, in

accordance with the Accomplishment

Instructions of Boeing Service Bulletin 767–

57–0021, dated August 25, 1988; Revision 1,

dated September 14, 1989; Revision 2, dated

July 26, 1990; or Revision 5, dated June 15,

1995.

(1) If the date of manufacture (stamped on

the control rod) is June 1983 or later, no

further action is required by this paragraph.

(2) If the date of manufacture is illegible or

is prior to June 1983, accomplish paragraphs

(a)(2)(i) and (a)(2)(ii) of this AD.

(i) Prior to further flight, perform an

ultrasonic inspection to detect cracks of the

control rods in accordance with Figure 1 of

Boeing Service Bulletin 767–57–0021, dated

August 25, 1988, Revision 1, dated

September 14, 1989, or Revision 2, dated July

26, 1990. If any crack or fracture is detected,

prior to further flight, replace it in

accordance with Figure 2 of the service

bulletin. Repeat the ultrasonic inspection of

the control rods manufactured prior to June

1983 thereafter at intervals not to exceed

2,000 landings or 15 months, whichever

occurs first, until the replacement required

by paragraph (a)(2)(ii) of this AD is

accomplished.

(ii) Within 3,000 flight hours or 15 months

after the effective date of this AD, whichever

occurs later, replace the control rod with a

new rod manufactured June 1983 or later, in

accordance with Boeing Service Bulletin

767–57–0021, Revision 5, dated June 15,

1995. Accomplishment of this replacement

constitutes terminating action for the

repetitive inspection requirement of

paragraph (a)(2)(i) of this AD.

(b) For airplanes having line number 1

through 264 inclusive, and 266 through 273

inclusive: Within the next 2,500 landings or

18 months after October 23, 1990 (the

effective date of AD 90–20–16, amendment

39–6726, whichever occurs first, replace the

control rod end and attach bolt with a new

configuration control rod end and attach bolt

on each wing, in accordance with Boeing

Service Bulletin 767–57–0221, Revision 1,

dated September 14, 1989; Revision 2, dated

July 26, 1990; or Revision 5, dated June 15,

1995.

(c) 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.

(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 airplane to

a location where the requirements of this AD

can be accomplished.

Issued in Renton, Washington, on

December 7, 1995.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 95–30353 Filed 12–12–95; 8:45 am]

BILLING CODE 4910–13–U
63992 Federal Register / Vol. 60, No. 239 / Wednesday, December 13, 1995 / Proposed Rules

14 CFR Part 39

[Docket No. 95–NM–244–AD]

Airworthiness Directives; Boeing

Model 767 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes the

adoption of a new airworthiness

directive (AD) that is applicable to all

Boeing Model 767 series airplanes. This

proposal would require inspections of

the components of the leading edge

outboard slat; replacement of the control

rod end, if necessary; and various

follow-on actions. This proposal is

prompted by reports of skewed panels

of the outboard leading edge slat due to

either corrosion of the rotary actuator,

cracking of the control rod, or incorrect

clearance of the overtravel stop of the

outboard leading edge slat. The actions

specified by the proposed AD are

intended to prevent such conditions,

which could result in reduced

controllability of the airplane and

damage to or cracking of the leading

edge slats or the fixed leading edge of

the wing.

DATES: Comments must be received by

January 24, 1996.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 95–NM–

244–AD, 1601 Lind Avenue SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

location between 9 a.m. and 3 p.m.,

Monday through Friday, except Federal

holidays.

This information may be examined at

the FAA, Transport Airplane

Directorate, 1601 Lind Avenue SW.,

Renton, Washington.

FOR FURTHER INFORMATION CONTACT:

Kristin Larson, Aerospace Engineer,

Systems and Equipment Branch, ANM–

130S, FAA, Seattle Aircraft Certification

Office, 1601 Lind Avenue SW., Renton,

Washington; telephone (206) 227–1760;

fax (206) 227–1181.

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 shall

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 Number 95–NM–244–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, Transport Airplane Directorate,

ANM–103, Attention: Rules Docket No.

95–NM–244–AD, 1601 Lind Avenue

SW., Renton, Washington 98055–4056.

Discussion

The FAA has received reports of

skewed panels of the outboard leading

edge slat on several Boeing Model 767

series airplanes. Investigation revealed

that the cause of the skewed panels is

attributed to either corrosion of the

rotary actuator, cracking of the control

rod, or incorrect clearance of the

overtravel stop of the outboard leading

edge slat. These conditions, if not

detected and corrected in a timely

manner, could result in reduced

controllability of the airplane and

damage to or cracking of the leading

edge slats or the fixed leading edge of

the wing.

Since an unsafe condition has been

identified that is likely to exist or

develop on other products of this same

type design, the FAA has determined

that an airworthiness directive (AD) is

warranted to require the following

inspections and follow-on actions of the

affected airplanes. These actions are

necessary in order to ensure that the

unsafe condition is corrected, and to

provide an acceptable level of safety:

1. A visual inspection to verify proper

clearance of the overtravel stop;

2. Adjustment of the stop clearance,

and replacement of the rotary actuator

and adjacent offset gearbox, if necessary;

3. Repetitive visual inspections to

detect external signs of internal

corrosion of the rotary actuator of the

outboard leading edge slat;

4. Replacement of a certain earlier

model rotary actuator with a certain

later model rotary actuator, for certain

airplanes;

5. Visual inspection(s) to verify

proper installation of the control rods of

the outboard leading edge slats; and

6. Tightening of the bolts or installing

a new lockwire, if any bolt is loose or

any lockwire is missing.

This proposed AD would require that

these actions be accomplished at

specific times and in accordance with

the procedures specified in the Boeing

767 Airplane Maintenance Manual

(AMM), Chapter 27–81–20.

This is considered to be interim

action. The manufacturer has advised

that it currently is developing a

modification that will positively address

the unsafe condition that is the subject

of this AD. Once this modification is

developed, approved, and available, the

FAA may consider additional

rulemaking.

There are approximately 612 Model

767 series airplanes of the affected

design in the worldwide fleet. The FAA

estimates that 213 airplanes of U.S.

registry would be affected by this

proposed AD, that it would take

approximately 14 work hours per

airplane to accomplish the proposed

actions, and that the average labor rate

is $60 per work hour. Based on these

figures, the cost impact of the proposed

AD on U.S. operators is estimated to be

$178,920, or $840 per airplane, per

inspection cycle.

The cost impact figure discussed

above is based on assumptions that no

operator has yet accomplished any of

the proposed requirements of this AD

action, and that no operator would

accomplish those actions in the future if

this AD were not adopted.

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
Federal Register / Vol. 60, No. 239 / Wednesday, December 13, 1995 / Proposed Rules 63993

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 USC 106(g), 40101, 40113,

44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

Boeing: Docket 95–NM–244–AD.

Applicability: All Model 767 series

airplanes, 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 use the authority

provided in paragraph (d) 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 airplane from the

applicability of this AD.

Compliance: Required as indicated, unless

accomplished previously.

To prevent reduced controllability of the

airplane and damage to or cracking of the

leading edge slats or the fixed leading edge

of the wing, accomplish the following:

(a) Within 500 hours time-in-service after

the effective date of this AD, unless

previously accomplished within the last

3,000 hours time-in-service prior to the

effective date of this AD: Perform a visual

inspection to verify proper clearance of the

overtravel stop, in accordance with the

Boeing 767 Airplane Maintenance Manual

(AMM), Chapter 27–81–20.

(1) If proper clearance exists, repeat the

inspection for proper clearance thereafter at

intervals not to exceed 6,000 hours time-inservice or 18 months, whichever occurs later.

(2) If clearance exists, but is incorrect, at

the next convenient maintenance interval,

but no later than 500 flight hours after

accomplishment of the inspection, adjust the

stop clearance for the slats in accordance

with the AMM. Repeat the inspection for

proper clearance thereafter at intervals not to

exceed 6,000 hours time-in-service or 18

months, whichever occurs later.

(3) If no clearance exists (i.e., stop contact),

prior to further flight, adjust the stop

clearance for the slats in accordance with the

AMM. After the adjustment, within 3,000

hours time-in-service or 1,500 flight cycles

after accomplishing the inspection required

by paragraph (a) of this AD, whichever

occurs later, replace the rotary actuator and

adjacent offset gearbox in accordance with

the AMM. After replacement, repeat the

inspection for proper clearance at intervals

not to exceed 6,000 hours time-in-service or

18 months, whichever occurs later.

(b) Within 500 hours time-in-service after

the effective date of this AD, unless

previously accomplished within the last

3,000 hours time-in-service prior to the

effective date of this AD, perform a visual

inspection to detect external signs of internal

corrosion of the rotary actuator of the

outboard leading edge slat, in accordance

with the Boeing 767 Airplane Maintenance

Manual (AMM), Chapter 27–81–20.

(1) If no sign of internal corrosion is

detected, accomplish paragraph (b)(1)(i) or

(b)(1)(ii) of this AD, as applicable.

(i) For airplanes on which a rotary actuator

having part number (P/N) 256T2120–3 or

earlier is installed: Within 4,000 flight hours

after the effective date of this AD, replace

that rotary actuator with a new rotary

actuator having P/N 256T2120–5 or later.

After replacement, repeat the inspection of

the rotary actuator at intervals not to exceed

6,000 flight hours or 18 months, whichever

occurs later.

(ii) For airplanes on which a rotary

actuator having P/N 256T2120–5 or later is

installed: Repeat the inspection of the rotary

actuator thereafter at intervals not to exceed

6,000 flight hours or 18 months, whichever

occurs later.

(2) If any sign of internal corrosion is

detected, accomplish paragraph (b)(2)(i) or

(b)(2)(ii) of this AD, as applicable.

(i) For airplanes on which a rotary actuator

having part number (P/N) 256T2120–3 or

earlier is installed: Within 4,000 flight hours

after the effective date of this AD, replace

that rotary actuator with a new rotary

actuator having P/N 256T2120–5 or later.

After replacement, repeat the inspection of

the rotary actuator at intervals not to exceed

6,000 flight hours or 18 months, whichever

occurs later.

(ii) For airplanes on which a rotary

actuator having P/N 256T2120–5 or later is

installed: Within 6,000 flight hours or 18

months after accomplishing the initial

inspection required by paragraph (b) of this

AD, replace that rotary actuator with a new

rotary actuator having P/N 256T2120–5 or

later. After replacement, repeat the

inspection required of the rotary actuator at

intervals not to exceed 6,000 flight hours or

18 months, whichever occurs later.

(c) Within 500 hours time-in-service after

the effective date of this AD, unless

previously accomplished within the last

3,000 hours time-in-service prior to the

effective date of this AD, perform a visual

inspection to verify proper installation

(including loose bolts and missing lockwires)

of the control rods of the outboard leading

edge slats, in accordance with the Boeing 767

Airplane Maintenance Manual (AMM),

Chapter 27–81–20.

(1) If all control rods are installed properly,

repeat the inspection to verify proper

installation thereafter at intervals not to

exceed 6,000 flight hours or 18 months,

whichever occurs later.

(2) If any bolt is loose or any lockwire

missing, prior to further flight, tighten the

bolt or install a new lockwire, in accordance

with the AMM. Repeat the inspection to

verify proper installation thereafter at

intervals not to exceed 6,000 flight hours or

18 months, whichever occurs later.

(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, 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.

(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.

Issued in Renton, Washington, on

December 7, 1995.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 95–30354 Filed 12–12–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 71

[Airspace Docket No. 95–AGL–20]

Establishment of Class E Airspace;

Bigfork, MN

AGENCY: Federal Aviation

Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking.

SUMMARY: This notice proposes to

establish Class E5 airspace at Bigfork

Municipal Airport, Bigfork, MN, to

accommodate a Nondirectional Radio