25608 Federal Register / Vol. 60, No. 92 / Friday, May 12, 1995 / Rules and Regulations

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 the following new airworthiness

directive:

95–10–05 Boeing: Amendment 39–9222.

Docket 94–NM–198–AD.

Applicability: Model 737–300, –400, and

–500 series airplanes; as listed in Boeing

Alert Service Bulletin 737–27A1191,

Revision 1, dated November 3, 1994;

certificated in any category.

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 use the authority

provided in paragraph (c) 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, accomplish the following:

(a) Within 12 months after the effective

date of this AD, replace the horizontal

stabilizer trim electric actuator having part

number 10–62033–3 with one that has been

modified and re-identified as P/N 10–62033–

4, in accordance with Boeing Alert Service

Bulletin 737–27A1191, Revision 1, dated

November 3, 1994.

(b) As of a date 6 months after the effective

date of this AD, no person shall install a

horizontal stabilizer trim electric actuator

having part number 10–62033–3 on any

airplane.

(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 §§ 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.

(e) The replacement shall be done in

accordance with Boeing Alert Service

Bulletin 737–27A1191, Revision 1, dated

November 3, 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 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.

(f) This amendment becomes effective on

June 12, 1995.

Issued in Renton, Washington, on May 3,

1995.

James V. Devany,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 95–11354 Filed 5–11–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 94–NM–239–AD; Amendment

39–9223; AD 95–10–06]

Airworthiness Directives; Bombardier

Model CL–600–1A11 (CL–600), –2A12

(CL–601), –2B16 (CL–601–3A, –3R),

and –2B19 (Regional Jet Series 100)

Series Airplanes, Equipped with

Sundstrand Air Driven Generator

(ADG) Uplock Assembly

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Bombardier Model

CL–600–1A11, –2A12, –2B16, and

–2B19 series airplanes, that requires an

inspection to verify the proper operation

of the uplock latch of the air driven

generator (ADG), and replacement of the

uplock latch with a serviceable part, if

necessary. This amendment also

requires replacing the uplock assembly

with a modified uplock assembly, and

performing a rigging inspection. This

amendment is prompted by a report

indicating that, upon operation of the

manual release system, the ADG did not

deploy due to failure of the shaft pin.

The actions specified by this AD are

intended to prevent failure of the shaft

pin, which could lead to the inability of

the pilot to manually deploy the ADG

when necessary (i.e., when an airplane’s

primary electrical power sources are lost

and the ADG fails to deploy

automatically).

DATES: Effective June 12, 1995.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of June 12,

1995.

ADDRESSES: The service information

referenced in this AD may be obtained

from Bombardier, Inc., Canadair

Aerospace Group, P.O. Box 6087,

Station Centre-ville, Quebec H3C 3G9,

Canada. This information may be

examined at the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, Rules Docket,

1601 Lind Avenue, SW., Renton,

Washington; or at the FAA, Engine and

Propeller Directorate, New York Aircraft

Certification Office, 10 Fifth Street,

Third Floor, Valley Stream New York;

or at the Office of the Federal Register,

800 North Capitol Street, NW., suite

700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Wing Chan, Electronics Engineer,

Systems and Equipment Branch, ANE–

173, FAA, Engine and Propeller

Directorate, New York Aircraft

Certification Office, 10 Fifth Street,

Third Floor, Valley Stream, New York

11581; telephone (516) 256–7511; fax

(516) 568–2716.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an airworthiness directive (AD)

that is applicable to certain Bombardier

Model CL–600–1A11, –2A12, –2B16,

and –2B19 series airplanes was

published in the Federal Register on

February 17, 1995 (60 FR 9302). That

action proposed to require a one-time

inspection to verify the proper operation

of the uplock latch of the air driven

generator (ADG), and replacement of the

uplock latch with a serviceable part if

the uplock latch cannot be activated.

That action also proposed to require

replacing the uplock assembly with a

modified uplock assembly, and

performing a rigging inspection.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

single comment received.

The commenter supports the

proposed rule.
Federal Register / Vol. 60, No. 92 / Friday, May 12, 1995 / Rules and Regulations 25609

After careful review of the available

data, including the comment noted

above, the FAA has determined that air

safety and the public interest require the

adoption of the rule as proposed.

The FAA estimates that 194 airplanes

of U.S. registry will be affected by this

AD, that it will take approximately 6

work hours per airplane to accomplish

the required actions, and that the

average labor rate is $60 per work hour.

Required parts will be supplied by the

manufacturer at no cost to the operators.

Based on these figures, the total cost

impact of the AD on U.S. operators is

estimated to be $69,840, or $360 per

airplane.

The total cost impact figure discussed

above is based on assumptions that no

operator has yet accomplished any of

the requirements of this AD action, and

that no operator would accomplish

those actions in the future if this AD

were not adopted.

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

adding the following new airworthiness

directive:

95–10–06 Bombardier Inc. (Formerly

Canadair): Amendment 39–9223. Docket

94–NM–239–AD.

Applicability: Model CL–600–1A11 (CL–

600) series airplanes, serial numbers 1004

through 1085 inclusive; Model CL–600–2A12

(CL–601) series airplanes, serial numbers

3001 through 3066 inclusive; Model CL–600–

2B16 (CL–601–3A, -3R) series airplanes,

serial numbers 5001 through 5150 inclusive;

Model CL–500–2B19 (Regional Jet Series 100)

series airplanes, serial numbers 7003 through

7040 inclusive; equipped with Sundstrand

air driven generator (ADG) uplock assembly

having part number 721863, 721863A, or

721863B; certificated in any category.

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 use the authority

provided in paragraph (c) 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 failure of the shaft pin, which

could lead to the inability of the pilot to

manually deploy the air driven generator

(ADG) when necessary (i.e., when an

airplane’s primary electrical power sources

are lost and the ADG fails to deploy

automatically), accomplish the following:

(a) For Model CL–600–2B19 (Regional Jet

Series 100) series airplanes equipped with

Sundstrand ADG uplock assembly having P/

N 721863B: Accomplish paragraphs (a)(1),

(a)(2), and (a)(3) of this AD in accordance

with Canadair Alert Service Bulletin S.B.

A601R–24–019, Revision ‘A’, dated August 9,

1994.

(1) Within 600 flight hours after the

effective date of this AD, perform an

inspection to verify the proper operation of

the uplock latch of the ADG, in accordance

with the Accomplishment Instructions of the

service bulletin. If the uplock latch cannot be

activated, prior to further flight, replace the

uplock latch with a serviceable part in

accordance with the alert service bulletin.

(2) Within 12 months after the effective

date of this AD, replace the uplock assembly

with a modified uplock assembly, in

accordance with the Accomplishment

Instructions of the alert service bulletin.

(3) After accomplishment of paragraph

(a)(1) or (a)(2) of this AD, perform a rigging

inspection in accordance with the

Accomplishment Instructions of the service

bulletin.

(b) For Model CL–600–2A12, CL–2B16,

and CL–600–1A11 series airplanes:

Accomplish paragraphs (b)(1), (b)(2), and

(b)(3) of this AD in accordance with Canadair

Service Bulletin 600–0638, dated April 25,

1994 (for Model CL–600–1A11 series

airplanes), or Canadair Service Bulletin 601–

0430, dated April 25, 1994 (for Model CL–

600–2A12 and –2B15 series airplanes), as

applicable.

(1) Within 150 flight hours after the

effective date of this AD, perform an

inspection to verify the proper operation of

the uplock latch of the ADG, in accordance

with the Accomplishment Instructions of the

applicable service bulletin. If the uplock

latch cannot be activated, prior to further

flight, replace the uplock latch with a

serviceable part, in accordance with the

applicable service bulletin.

(2) Within 12 months after the effective

date of this AD, replace the uplock assembly

with a modified uplock assembly, in

accordance with the Accomplishment

Instructions of the applicable service

bulletin.

(3) After accomplishment of paragraph

(b)(1) or (b)(2) of this AD, perform a rigging

inspection in accordance with the

Accomplishment Instructions of the

applicable service bulletin.

(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, New York

Aircraft Certification Office (ACO), FAA,

Engine and Propeller Directorate. Operators

shall submit their requests through an

appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, New York ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the New York ACO.

(d) 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 the airplane to a

location where the requirements of this AD

can be accomplished.

(e) The actions shall be done in accordance

with Canadair Alert Service Bulletin S.B.

A601R–24–019, Revision ‘A’, dated August 9,

1994; Canadair Service Bulletin 600–0638,

dated April 25, 1994; or Canadair Service

Bulletin 601–0430, dated April 25, 1994; as

applicable. 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 Bombardier, Inc., Canadair Aerospace

Group, P.O. Box 6087, Station Centre-ville,

Quebec H3C 3G9, Canada. Copies may be
25610 Federal Register / Vol. 60, No. 92 / Friday, May 12, 1995 / Rules and Regulations

inspected at the FAA, Transport Airplane

Directorate, 1601 Lind Avenue, SW., Renton,

Washington; or at the FAA, Engine and

Propeller Directorate, New York Aircraft

Certification Office, 10 Fifth Street, Third

Floor, Valley Stream New York; or at the

Office of the Federal Register, 800 North

Capitol Street, NW., suite 700, Washington,

DC.

(f) This amendment becomes effective on

June 12, 1995.

Issued in Renton, Washington, on May 3,

1995.

James V. Devany,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 95–11355 Filed 5–11–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 94–NM–175–AD; Amendment

39–9219; AD 95–10–02]

Airworthiness Directives; McDonnell

Douglas Model MD–11 Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain McDonnell

Douglas MD–11 series airplanes, that

requires the installation of an

electrically controlled slat system. This

amendment is prompted by numerous

incidents of inadvertent deployment of

the slats while the airplane was in flight

at cruise altitude. The actions specified

by this AD are intended to prevent

inadvertent deployment of the slats

during flight, which could result in an

abrupt pitch up of the airplane and

consequent injury to crew and

passengers; it could also result in

significant vibrations and cause damage

to the elevators.

DATES: Effective June 12, 1995.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of June 12,

1995.

ADDRESSES: The service information

referenced in this AD may be obtained

from McDonnell Douglas Corporation,

P.O. Box 1771, Long Beach, California

90801–1771, Attention: Business Unit

Manager, Technical Administrative

Support, Dept. L51, M.C. 2–98. This

information may be examined at the

Federal Aviation Administration (FAA),

Transport Airplane Directorate, Rules

Docket, 1601 Lind Avenue, SW.,

Renton, Washington; or the FAA, Los

Angeles Aircraft Certification Office,

Transport Airplane Directorate, 3960

Paramount Boulevard, Lakewood,

California; or at the Office of the Federal

Register, 800 North Capitol Street, NW.,

suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Wahib Mina, Aerospace Engineer,

Airframe Branch, ANM–120L, Los

Angeles Aircraft Certification Office,

FAA, Transport Airplane Directorate,

3960 Paramount Boulevard, Lakewood,

California 90712–4137; telephone (310)

627–5324; fax (310) 627–5210.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an airworthiness directive (AD)

that is applicable to Model MD–11

series airplanes; as listed in McDonnell

Douglas MD–11 Service Bulletin 27–36,

Revision 1, dated December 9, 1994 was

published in the Federal Register on

January 6, 1995 (60 FR 2041). That

action proposed to require installation

of an electrically controlled slat system.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the two

comments received.

One commenter supports the

proposed rule.

The other commenter supports the

rule, but disagrees with the FAA’s

estimate of the number of work hours

that would be required to accomplish

the installation. In the preamble to the

proposal, the FAA indicated that the

time necessary to perform the

installation would be approximately 68

work hours; however, the commenter

indicates that a more reasonable

estimate is closer to 200 work hours.

The FAA does not concur with the

commenter’s revised estimate, since the

commenter provided no additional

information to support it. The FAA’s

original estimate of labor time was

based on data provided by the

manufacturer at the time the proposal

was developed. Upon further review of

that data, however, the FAA finds that

the most accurate estimate of the time

necessary to accomplish the installation

is 75 work hours. This number includes

4 work hours to gain access; 8 work

hours to remove components; 51 work

hours for modification of mechanical

and electrical components; 4 work

hours for installation; 4 work hours for

closing up; and 4 work hours for a

functional check. The cost analysis

information, described below, has been

revised to indicate that 75 work hours

are necessary for accomplishment of the

required installation. In general, the cost

analysis in AD rulemaking actions

typically does not include planning

time, time for administrative functions,

nonproductive elapsed time, or aircraft

preparation time.

As a result of recent communications

with the Air Transport Association

(ATA) of America, the FAA has learned

that, in general, some operators may

misunderstand the legal effect of AD’s

on airplanes that are identified in the

applicability provision of the AD, but

that have been altered or repaired in the

area addressed by the AD. The FAA

points out that all airplanes identified in

the applicability provision of an AD are

legally subject to the AD. If an airplane

has been altered or repaired in the

affected area in such a way as to affect

compliance with the AD, the owner or

operator is required to obtain FAA

approval for an alternative method of

compliance with the AD, in accordance

with the paragraph of each AD that

provides for such approvals. A note has

been added to this final rule to clarify

this long-standing requirement.

After careful review of the available

data, including the comments noted

above, the FAA has determined that air

safety and the public interest require the

adoption of the rule with the changes

previously described. The FAA has

determined that these changes will

neither increase the economic burden

on any operator nor increase the scope

of the AD.

There are approximately 124 Model

MD–11 series airplanes of the affected

design in the worldwide fleet. The FAA

estimates that 43 airplanes of U.S.

registry will be affected by this AD, that

it will take approximately 75 work

hours per airplane to accomplish the

required actions, and that the average

labor rate is $60 per work hour.

Required parts will be supplied by the

manufacturer at no charge to operators.

Based on these figures, the total cost

impact of the AD on U.S. operators is

estimated to be $193,500, or $4,500 per

airplane.

The total cost impact figure discussed

above is based on assumptions that no

operator has yet accomplished any of

the requirements of this AD action, and

that no operator would accomplish

those actions in the future if this AD

were not adopted.

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.