Federal Register / Vol. 63, No. 150 /Wednesday, August 5, 1998 / Proposed Rules 41741

been eliminated, the request should include

specific proposed actions to address it.

Compliance: Required as indicated, unless

accomplished previously.

To prevent corrosion of the forward

trunnion joint of the main landing gear

(MLG), which could lead to a stress corrosion

fracture of the forward trunnion and possible

consequent collapse of the MLG, accomplish

the following:

(a) Within 6 years since the outer cylinder

of the MLG was new, last overhauled, or

installed (replaced) after the last corrosion

repair in accordance with Boeing Alert

Service Bulletin 767–32A0127, dated January

29, 1996; or within 18 months after the

effective date of this AD; whichever occurs

later: Perform a detailed visual inspection to

detect corrosion inside the forward trunnion

joint and the internal threads of the MLG; in

accordance with the Accomplishment

Instructions of Boeing Alert Service Bulletin

767–32A0127, dated January 29, 1996.

(1) If no corrosion of the forward trunnion

joint is found, prior to further flight,

accomplish either paragraph (a)(1)(i) or

(a)(1)(ii) of this AD.

(i) Apply chrome plating to the forward

trunnion thrust and tab faces in accordance

with the alert service bulletin.

Accomplishment of this application of

chrome plating constitutes terminating action

for the requirements of this AD.

(ii) Apply corrosion-inhibiting compound

to the forward trunnion joint in accordance

with the Accomplishment Instructions of the

alert service bulletin. Repeat the detailed

visual inspection thereafter at intervals not to

exceed six years or until chrome plating is

applied to the forward trunnion thrust and

tab faces in accordance with the alert service

bulletin.

(2) If any corrosion of the forward trunnion

joint is found, prior to further flight,

accomplish either paragraph (a)(2)(i) or

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

(i) Repair the forward trunnion and apply

chrome plating to the forward trunnion

thrust and tab faces in accordance with the

alert service bulletin. Accomplishment of

this application of chrome plating constitutes

terminating action for the requirements of

this AD.

(ii) Repair the forward trunnion and apply

corrosion-inhibiting compound to the

forward trunnion joint in accordance with

the alert service bulletin. Repeat the detailed

visual inspection thereafter at intervals not to

exceed six years or until chrome plating is

applied to the forward trunnion thrust and

tab faces in accordance with the alert service

bulletin.

(b) Replacement, repair, or overhaul of the

outer cylinder of the MLG that includes the

application of chrome plating to the forward

trunnion thrust and tab faces in accordance

with Boeing Alert Service Bulletin 767–

32A0127, dated January 29, 1996, constitutes

terminating action for the requirements of

this AD.

(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 July 29,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–20834 Filed 8–4–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–04–AD]

RIN 2120–AA64

Airworthiness Directives; de Havilland

Model DHC–8–100, –200, and –300

Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Supplemental notice of

proposed rulemaking; reopening of

comment period.

SUMMARY: This document revises an

earlier proposed airworthiness directive

(AD), applicable to certain de Havilland

Model DHC–8–100, –200, and –300

series airplanes, that would have

required modification of the flight

compartment door. That proposal was

prompted by a report that the door lock

mechanism of the flight compartment

door jammed and could not be opened

using the alternate release mechanism.

This new action would add repetitive

inspections for wear of the flight

compartment door hinges following

modification, and repair or replacement

of the hinges with new hinges, if

necessary. This new action also revises

the applicability of the existing AD. The

actions specified by this new proposed

AD are intended to prevent failure of the

alternate release mechanism of the flight

compartment door, which could delay

or impede the evacuation of the

flightcrew during an emergency. Such

failure also could result in the

flightcrew not being able to assist

passengers in the event of an

emergency.

DATES: Comments must be received by

August 31, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 97–NM–

04–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

location between 9:00 a.m. and 3:00

p.m., Monday through Friday, except

Federal holidays.

The service information referenced in

the proposed rule may be obtained from

Bombardier, Inc., Bombardier Regional

Aircraft Division, Garratt Boulevard,

Downsview, Ontario M3K 1Y5, Canada.

This information may be examined 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.

FOR FURTHER INFORMATION CONTACT: Ezra

Sasson, Aerospace Engineer, Systems

and Equipment Branch, ANE–172, FAA,

New York Aircraft Certification Office,

Engine and Propeller Directorate, 10

Fifth Street, Third Floor, Valley Stream,

New York 11581; telephone (516) 256–

7520; fax (516) 568–2716.

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
41742 Federal Register / Vol. 63, No. 150 /Wednesday, August 5, 1998 / Proposed Rules

statement is made: ‘‘Comments to

Docket Number 97–NM–04–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–114, Attention: Rules Docket No.

97–NM–04–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

A proposal to amend part 39 of the

Federal Aviation Regulations (14 CFR

part 39) to add an airworthiness

directive (AD), applicable to certain de

Havilland Model DHC–8–100, –200, and

–300 series airplanes, was published as

a notice of proposed rulemaking

(NPRM) in the Federal Register on July

11, 1997 (62 FR 37170). That NPRM

would have required modification of the

flight compartment door. That NPRM

was prompted by a report that the door

lock mechanism of the flight

compartment door jammed and it could

not be opened using the alternate

release mechanism. That condition, if

not corrected, could result in failure of

the alternate release mechanism of the

flight compartment door, which could

delay or impede the evacuation of the

flightcrew during an emergency. Such

failure also could result in the

flightcrew not being able to assist

passengers in the event of an

emergency.

Actions Since Issuance of Previous

Proposal

Since the issuance of that NPRM, the

manufacturer has issued de Havilland

Service Bulletin S.B. 8–52–39, Revision

‘C,’ dated September 1, 1997, and

Revision ‘D,’ dated February 27, 1998.

Among other things, Revision ‘C’

revises the effectivity of the earlier

releases of the service bulletin. In

addition, the Accomplishment

Instructions of the service bulletin have

been revised to include a section titled

‘‘Special Inspection/Repair,’’ which

describes procedures for repetitive

inspections of the door hinges for wear.

For airplanes on which any wear is

found that is greater than 0.050 inch in

depth, the service bulletin describes

procedures for removal and replacement

of the hinges with new hinges. For

airplanes on which any wear is found

that is less than 0.050 inch, but greater

than 0.020 inch in depth, the service

bulletin describes procedures for repair

of the hinge.

Revision ‘D’ is essentially identical to

Revision ‘C;’ however, it provides

information for an additional

modification kit for certain Model DHC–

8–300 series airplanes with a forward

galley where a –100 series lavatory has

been installed.

Transport Canada Aviation, which is

the airworthiness authority for Canada,

classified these service bulletin

revisions as mandatory and issued

Canadian airworthiness directive CF–

96–20R2, dated July 16, 1997, in order

to assure the continued airworthiness of

these airplanes in Canada.

Changes to the Original NPRM

The FAA has determined that, in

order to adequately address the unsafe

condition presented by problems

associated with the flight compartment

door, the originally proposed rule must

be revised to require repetitive

inspections for wear of the modified

flight compartment door hinges, and

repair, if necessary. These additional

actions would be required to be

accomplished in accordance with the

revised service bulletins described

previously.

Additionally, the applicability of this

supplemental NPRM has been revised to

correspond with the revised service

bulletin effectivity discussed

previously.

Conclusion

Since these changes expand the scope

of the originally proposed rule, the FAA

has determined that it is necessary to

reopen the comment period to provide

additional opportunity for public

comment.

Interim Action

This is considered to be interim

action. The manufacturer has advised

the FAA that it currently is developing

a modification that will eliminate the

need for the repetitive inspections for

wear of the flight compartment door

hinges. Once this modification is

developed, approved, and available, the

FAA may consider additional

rulemaking.

Cost Impact

The FAA estimates that 133 de

Havilland Model DHC–8–100, –200, and

–300 series airplanes of U.S. registry

would be affected by this proposed AD.

It would take approximately 4 work

hours per airplane to accomplish the

proposed modification, at an average

labor rate of $60 per work hour.

Required parts would be provided by

the manufacturer at no cost to operators.

Based on these figures, the cost impact

of the modification proposed by this AD

on U.S. operators is estimated to be

$31,920, or $240 per airplane.

It would take approximately 2 work

hours per airplane to accomplish the

proposed inspection, at an average labor

rate of $60 per work hour. Based on

these figures, the cost impact of the

inspection proposed by this AD on U.S.

operators is estimated to be $15,960, or

$120 per airplane, per inspection cycle.

The cost impact figures discussed

above are 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.

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 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. 106(g), 40113, 44701.
Federal Register / Vol. 63, No. 150 /Wednesday, August 5, 1998 / Proposed Rules 41743

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

De Havilland, Inc.: Docket 97–NM–04–AD.

Applicability: Model DHC–8–100, –200,

and –300 series airplanes having serial

numbers 3 and subsequent; 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 request approval for an

alternative method of compliance in

accordance with paragraph (c) 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 as indicated, unless

accomplished previously.

To prevent failure of the alternate release

mechanism of the flight compartment door,

which could delay or impede the evacuation

of the flightcrew and passengers during an

emergency, accomplish the following:

(a) Within 90 days after the effective date

of this AD, modify the lower hinge assembly

and main door latch (Modification 8/2337) of

the flight compartment door, in accordance

with de Havilland Service Bulletin S.B. 8–

52–39, Revision ‘D,’ dated February 27, 1998.

Note 2: Modification of the flight

compartment door accomplished prior to the

effective date of this AD in accordance with

de Havilland Service Bulletin S.B. 8–52–39,

dated August 30, 1996; Revision ‘A,’ dated

October 31, 1996; Revision ‘B,’ dated July 4,

1997; or Revision ‘C,’ dated September 1,

1997; is considered acceptable for

compliance with the modification required

by paragraph (a) of this AD.

(b) Within 800 flight hours after

accomplishment of the modification required

by paragraph (a) of this AD, inspect the hinge

areas around the hinge pin holes of the flight

compartment door for wear, in accordance

with de Havilland Service Bulletin S.B. 8–

52–39, Revision ‘C,’ dated September 1, 1997,

or Revision ‘D,’ dated February 27, 1998.

(1) If no wear is detected, or if the wear is

less than or equal to 0.020 inch in depth,

repeat the inspection thereafter at intervals

not to exceed 800 flight hours.

(2) If any wear is detected and its

dimension around the hinge pin holes is less

than 0.050 inch and greater than 0.020 inch

in depth, prior to further flight, perform the

applicable corrective actions specified in the

service bulletin. Repeat the inspection

thereafter at intervals not to exceed 800 flight

hours.

(3) If any wear is detected and its

dimension around the hinge pin holes is

greater than or equal to 0.050 inch in depth,

prior to further flight, replace the worn

hinges with new hinges in accordance with

the service bulletin. Repeat the inspection

thereafter at intervals not to exceed 800 flight

hours.

(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 3: 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 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.

Note 4: The subject of this AD is addressed

in Canadian airworthiness directive CF–96–

20R2, dated July 16, 1997.

Issued in Renton, Washington, on July 29,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–20833 Filed 8–4–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Parts 65, 66, and 147

[Docket No. 27863; Notice No. 98–5]

RIN 2120–AF22

Revision of Certification

Requirements: Mechanics and

Repairmen; Correction

AGENCY: Federal Aviation

Administration (FAA), DOT.

ACTION: Notice of Proposed Rulemaking

(NPRM); correction.

SUMMARY: This document corrects the

preamble to a proposed rule published

in the Federal Register on July 9, 1998,

(63 FR 37172) that would revise the

certification requirements for mechanics

and repairmen. This correction provides

the public with the correct telephone

number to obtain a copy of the NPRM.

FOR FURTHER INFORMATION CONTACT:

Leslie K. Vipond, AFS–350, Continuous

Airworthiness Maintenance Division,

Flight Standards Service, Federal

Aviation Administration, 800

Independence Avenue SW., Washington

DC 20591, telephone: (202) 267–3269.

Correction

In proposed rule FR Doc. 98–17589

beginning on page 37172 in the Federal

Register issue of Thursday, July 9, 1998,

make the following correction:

On page 37172, in the Availability of

NPRMs section, in the third column, in

the second complete paragraph, on line

7, the telephone number specified to

obtain a copy of the NPRM is listed as

‘‘(202) 267–9860.’’ This should be

changed to read ‘‘(202) 267–9680.’’

Issued: in Washington, DC on July 31,

1998.

Donald P. Byrne,

Assistant Chief Counsel, Regulations

Division.

[FR Doc. 98–20934 Filed 8–4–98; 8:45 am]

BILLING CODE 4910–13–M

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 71

[Airspace Docket No. 95–AWA–12]

RIN 2120–AA66

Proposed Modification of the Salt Lake

City Class B Airspace Area; Utah

AGENCY: Federal Aviation

Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This action proposes to

modify the Salt Lake City, UT, Class B

airspace area. Specifically, this action

proposes to reconfigure three existing

subarea boundaries. The FAA is

proposing this action to enhance safety

and improve the flow of air traffic into,

out of, through, and around the Salt

Lake City Class B airspace area, while

accommodating the concerns of airspace

users.

DATES: Comments must be received on

or before October 5, 1998.

ADDRESSES: Send comments on the

proposal in triplicate to the Federal

Aviation Administration, Office of the

Chief Counsel, Attention: Rules Docket,

AGC–200, Airspace Docket No. 95–

AWA–12, 800 Independence Avenue,

SW., Washington DC 20591. Comments

may also be sent electronically to the

following Internet address: 9–NPRM–

CMTS@faa.dot.gov. The official docket

may be examined in the Rules Docket,

Office of the Chief Counsel, Room 916,

800 Independence Avenue, SW.,

Washington, DC, weekdays, except

Federal holidays, between 8:30 a.m. and

5:00 p.m. An informal docket may also

be examined during normal business

hours at the Office of the Regional Air

Traffic Division.

FOR FURTHER INFORMATION CONTACT: Ken

McElroy, Airspace and Rules Division,